| With the development of the war situation, the growing requirements of the projectile and rocket weapon reverse-fuzzy strike capability are put forward in many countries all over the world. The accurate level of the missile has grown up, which can meet the demand of the battlefield. But, the missile is so expensive that makes the costs of the war is too high, and many countries can’t have a lot of equipment. At the same time, the stock of rotational-stability projectile is huge all over the world. If these projectiles are guided modification on a low cost,and it’s hit precision can be improved, that must be of great significance. In this paper, we regard a rotational stabilitied projectile, which has canard-control and dual-spin structure, as the research object. The study of its flight mechanics properties mainly includes the following aspects:1. Because the front and after part of the canard guided dual-spin projectile have a different moment of inertia, which causes a different rotational speed in the progress of flight between the two parts of the projectile. I set up a seven degrees of freedom ballistic model in the basis of the regular spin-stabilized-projectile 6D model. First of all, in the condition of equal mass, symmetry of geometric shape about projectile vertical axis and the center of front, after and the whole part collinear, a simplifying seven degrees of freedom model is founded. Secondly, considering the three centers of mass have the general situation that they aren’t collinear and using the parallel axis theorem of moment of inertia matrix, a universal seven degrees of freedom ballistic model is established.2. I have designed a couple of different rudder yaw-angle canard guided dual-spin projectile models. By using Computational fluid dynamic methods and software, the aerodynamic simulation on this group of models is done under the condition of subsonic, transonic and supersonic. The drag coefficient, lift coefficient, pitching moment coefficient and roll moment coefficient changing rule with the Mach number is calculated, and the curve has been drawn. At the same time, I also obtain the flow field distribution of different rudder yaw-angle model. Thus aerodynamic characteristics of the canard guided dual-spin projectile are analyzed.3. The variation rules of ballistic parameters during the free flight are studied about the canard guided dual-spin projectile. In controlled conditions, the projectile ballistic curve changing rule,pitching angle changing rule and angle of attack characteristics changing rule under the same control phase angle and different start control time are investigated. Changing the control signal phase angle of the projectile and doing the trajectory characteristic simulation,we can see the influence of the change of the phase angle on the ballistic characteristic. At the same time, the correction ability on different time is also studied in order to get better correction effect.4. The complex angle equation of motion, rotation rate movement differential equation and compound pendulum motion equation are deduced, based on which the linearization angle of attack motion equations of the dual-spin stabilized projectile with canards are deduced,and the angle motion characteristics is studied.In the last time, the gyroscopic stability, trucking stability and dynamic stability about this projectile are studied. Through computer simulation, the conclusion that the canard guided dual-spin projectile has enough stability is obtained.5. By using the linearization methods, the transfer function of the studied projectile is deduced on the basis of the seven degrees of freedom ballistic model. The transition process of this projectile is analyzed when the canard doing step deflection. What’s more, the frequency characteristics of the projectile are studied in this article. Through the analysis of the parameters such as phase margin, cut-off frequency, it is concluded that the stability of the system and the conclusion of quickening the response of the system. |
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