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An Analysis Method of Geometric Nonlinear Lower Angular Motion Characteristics of Double Spinning Projectiles

A technique of geometric nonlinearity and characteristic analysis, which is applied in the field of double-spin angular motion characteristic analysis, and can solve the problems of nonlinear motion phenomena, which are difficult to theoretical analysis and interpretation of linear systems.

Active Publication Date: 2022-07-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0003] However, compared with the mature design methods of fin-stabilized bombs, there are still many problems to be solved urgently in the analysis of dynamic characteristics of dual-rotor bombs
In particular, the double-rotation elastic dynamics has the characteristics of strong coupling and strong nonlinearity, which makes it difficult to analyze and explain many nonlinear motion phenomena of projectiles with linear system theory.

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  • An Analysis Method of Geometric Nonlinear Lower Angular Motion Characteristics of Double Spinning Projectiles
  • An Analysis Method of Geometric Nonlinear Lower Angular Motion Characteristics of Double Spinning Projectiles
  • An Analysis Method of Geometric Nonlinear Lower Angular Motion Characteristics of Double Spinning Projectiles

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Embodiment Construction

[0063] Examples are given below to describe the present invention in detail.

[0064] This embodiment provides a method for analyzing the geometric nonlinear lower angular motion characteristics of a dual-rotor projectile. Taking the deflection angle of the yaw rudder as a bifurcation parameter, the boundary conditions for the dynamic instability of the dual-rotor projectile are given, and the angle at the critical point is determined. For the bifurcation phenomenon caused by motion, the central manifold theorem is used to reduce the dimensionality of the angular motion near the bifurcation point. Through the reduction and analysis of the equation, the variation law of the equilibrium state near the bifurcation point is obtained.

[0065] The analysis method mainly includes the following steps:

[0066] Step 1: Establish the angle of attack α, sideslip angle β, and pitch angular velocity ω of the double-spin projectile z , yaw angular velocity ω y The nonlinear angular equat...

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Abstract

The invention discloses a method for analyzing the geometric nonlinear lower angular motion characteristics of a dual-rotation projectile. z , yaw angular velocity ω y The nonlinear angular motion equation of ; Step 2: Use the pitch angle δ z and the yaw rudder angle δ y As a parameter, determine the Jacobian matrix of the angular motion system in the equilibrium state corresponding to the nonlinear angular motion equation established in step 1; step 3: determine the sufficient and necessary conditions for the stability of the angular motion system in the equilibrium state; step 4: determine the angle The boundary conditions that the yaw rudder declination angle needs to meet when the motion system is stable; Step 5: Perform dimensionality reduction processing on the angular motion system, through the reduction and analysis of the nonlinear angular motion equation described in Step 1, to determine the double spinner in the equilibrium state Motion characteristics around the bifurcation point.

Description

technical field [0001] The invention relates to the technical field of analysis of the angular motion characteristics of a double-spin projectile, in particular to a method for analyzing the geometric nonlinear lower angular movement characteristics of a double-spin projectile. Background technique [0002] The large demand for high-precision, low-cost, over-the-horizon, and small collateral damage guided munitions in modern warfare has promoted the rapid development of conventional artillery shell guidance technology. For the rotationally stabilized projectile, in order to achieve the ideal control effect and meet the requirements of the rotationally stabilized projectile for the high speed of the projectile, an effective method is to divide the projectile into two parts, namely the front body and the rear body, which are connected by bearings. , during the flight, the front body and the rear body rotate at different speeds, so it is called "double rotation". This double-r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/14Y02T90/00
Inventor 沈元川于剑桥贾振岳陈曦
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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