Full strapdown guidance and control integrated design method based on three-order model

A design method and model technology, applied in the aerospace field, can solve problems such as lack of system stability guarantee, complex integrated algorithm, controller cycle design, etc., to avoid controller cycle design problems, overcome controller complexity problems and The effect of system stability problems

Active Publication Date: 2020-12-01
HARBIN INST OF TECH
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Problems solved by technology

There are two main problems in this type of method: one is that the state variables such as pitch (yaw) angular rate are treated as bounded disturbances, which lack strict system stability guarantees; Algorithms are relatively comp

Method used

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  • Full strapdown guidance and control integrated design method based on three-order model
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  • Full strapdown guidance and control integrated design method based on three-order model

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Embodiment

[0086] Here, a certain representative embodiment is introduced to further illustrate the relevant design in the technical solution of the present invention.

[0087] The designed integrated guidance and control algorithm considering the constraints of the field of view of the strapdown seeker is applied to the nonlinear guidance and control system of the missile in the longitudinal plane as shown below:

[0088]

[0089] In the formula, the drag X, lift Y and pitching moment M of the missile z The calculation formula is: Among them, c x0 is the zero-lift drag coefficient, Respectively drag coefficient relative to α, δ z partial derivative of .

[0090] In the simulation, the structural and aerodynamic parameters of the missile are set as: S=0.42m 2 , L=0.68m, m=1200Kg, J z =5600Kg·m 2 , P=5000N, Let the target be a slow moving target on the ground, and the velocity is V t =10m / s, target ballistic inclination angle is θ t = 0°, assume that the initial velocity...

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Abstract

The invention discloses a full-strapdown guidance and control integrated design method based on a three-order model. The method comprises the following steps: step 1, establishing a three-order guidance and control integrated design model; step 2, clearly considering a design task of a guidance and control integrated algorithm considering full strapdown seeker view field constraints; step 3, constructing an auxiliary system, designing a first-layer expected virtual control quantity eta d, and processing the first-layer expected virtual control quantity eta d through an approximate saturation function to obtain a first-layer virtual control quantity eta c; step 4, designing a second-layer virtual control quantity omega zc by utilizing a Barrier Lyapunov function; step 5, designing an actualrudder deflection angle instruction delta z; step 6, integrating the steps 3-5 to obtain the guidance and control integrated algorithm considering view field constraints; and step 7, checking the performance of the guidance and control integrated algorithm. The method can completely achieve a target, and guarantees that the full strapdown seeker view field constraints are satisfied.

Description

technical field [0001] The invention belongs to the field of aerospace, and relates to an integrated guidance and control design method, in particular to an integrated guidance and control design method based on a third-order model considering the field of view constraint of a strapdown seeker. Background technique [0002] It is of great significance to carry out the research on the integrated design of guidance and control under the all-strapdown detection and guidance system for the development of low-cost and high-performance tactical missiles. An important problem in the integrated design of strapdown guidance and control is to deal with the constraints of the seeker's field of view. From the perspective of the established guidance and control integrated design model, the main progress in this field includes the fourth-order model method and the second-order model method. The fourth-order model method is based on literature 1 "The guidance and control integrated design...

Claims

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Application Information

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IPC IPC(8): F42B15/01F41G7/00
CPCF41G7/00F42B15/01
Inventor 侯明哲吴爱国石文锐段广仁
Owner HARBIN INST OF TECH
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