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An aerodynamic shape design method for a dual-rotation stabilized projectile based on a fixed-wing canard rudder

A technology of aerodynamic shape and design method, applied in the field of aerospace, can solve the problems of high cost, unsuitable aerodynamic shape design of fixed-wing canard rudder, etc., and achieve the effect of improving landing accuracy

Inactive Publication Date: 2020-04-14
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

For the accuracy of mortar shells, in the prior art, the cross canard rudder is mainly used to realize the precise guidance of the shell. Not suitable for aerodynamic shape design of fixed-wing canards

Method used

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  • An aerodynamic shape design method for a dual-rotation stabilized projectile based on a fixed-wing canard rudder
  • An aerodynamic shape design method for a dual-rotation stabilized projectile based on a fixed-wing canard rudder
  • An aerodynamic shape design method for a dual-rotation stabilized projectile based on a fixed-wing canard rudder

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Embodiment Construction

[0036] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be described in further detail below with reference to the accompanying drawings and preferred embodiments. However, it should be noted that many of the details listed in the specification are only for readers to have a thorough understanding of one or more aspects of the present invention, and these aspects of the present invention can be implemented even without these specific details.

[0037] This embodiment provides an aerodynamic shape design method for a dual-rotation stabilized missile based on a fixed-wing canard. The schematic diagram of the shape of the dual-rotation stabilized missile is as follows figure 2 As shown, its flow chart is as follows figure 1 As shown, the rudder area S of the fixed-wing canard rudder is calculated respectively C , Pitch rudder angle setting value δ Z and the distance X from the center of pressure to the ...

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Abstract

The invention discloses an aerodynamic configuration design method for a bi-rotational stable ball based on a fixed wing canard rudder. According to the method, after a rudder area SC, a pitching rudder angle setting value delta Z and the distance XC from a pressure center to a ball mass center of the fixed wing canard rudder are calculated respectively, the maximum value of the lift-to-drag ratio KL / D is solved according to formed constraint conditions; then, a rolling rudder angle setting value delta y and an empennage chamfer angle are determined according to internal and external friction moments of the fixed wing canard rudder and the moment balancing relation between an electromagnetic resistance moment and an aerodynamic moment; and the lift-to-drag ratio KL / D is adjusted under the condition that the rolling rudder angle setting value delta y and the empennage chamfer angle are determined to realize attitude adjustment of a mortar.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to an aerodynamic shape design method of a double-spin stabilized projectile based on a fixed-wing canard. Background technique [0002] Mortars have the characteristics of curved trajectory, fast rate of fire, simple structure, easy maneuverability, and easy operation. They are suitable for urban street fighting and mountain warfare, and have been widely used in countries all over the world. For the accuracy of mortar shells, in the prior art, the cross canard rudder is mainly used to realize the precise guidance of the shell. It is not suitable for the aerodynamic shape design of fixed-wing canards. Contents of the invention [0003] Aiming at the defects in the above-mentioned prior art, the present invention provides an aerodynamic shape design method for a double-spin stabilized projectile based on a fixed-wing canard, which rationally utilizes the external aerodynamic force of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17F42B10/06F42B10/64
CPCF42B10/06F42B10/64G06F30/17Y02T90/00
Inventor 张衍儒肖练刚田丰陈昌周华王婧邱奕
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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