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Guidance and control integrated design method considering all-strapdown seeker view field constraint

A design method and seeker technology, applied in attitude control, non-electric variable control, control/regulation system, etc., can solve problems such as poor practicability

Inactive Publication Date: 2017-05-17
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the shortcomings of poor practicability of the existing integrated guidance and control design method, the present invention provides an integrated guidance and control design method considering the constraints of the field of view of the strapdown seeker

Method used

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Embodiment 1

[0066] The specific steps of the guidance and control integrated design method considering the constraints of the field of view of the strapdown seeker in the present invention are as follows:

[0067] Step 1. Establish a state space model for system design, which consists of three parts: missile longitudinal channel attitude control system model, missile-target relative motion model in the longitudinal plane, and strapdown seeker longitudinal channel line of sight decoupling model.

[0068] (a) Model of missile longitudinal channel attitude control system.

[0069]

[0070] Among them, α is the flight angle of attack of the missile, ω z is the pitch angular velocity of the missile, δ is the pitch rudder deflection angle of the missile; P is the engine thrust of the missile, m is the mass of the missile, J z is the moment of inertia of the missile, V M is the flight speed of the missile; q is the flight dynamic pressure of the missile, S is the reference area of ​​the mis...

Embodiment 2

[0113] The value of the extended state observer in step 2 of this embodiment is:

[0114] alpha 1 = α 2 = α 3 = α 4 =0.3,β 10 = β 20 =20,β 30 = β 40 =10

[0115] beta 11 = β 21 = β 31 = β 41 =50,σ 1 = σ 2 = σ 3 = σ 4 =0.05

[0116] Other steps and parameters are the same as in Example 1.

Embodiment 3

[0117] Embodiment 3: K in step 3 of this embodiment 1 =10,Q=20 / 57.3,τ 2 =0.025,η 1 = 0.001.

[0118] Other steps and parameters are the same as in Example 1.

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Abstract

The invention discloses a guidance and control integrated design method considering all-strapdown seeker view field constraint, and aims at solving the technical problem that an existing guidance and control integrated design method is poor in practicability. According to the technical scheme, the guidance and control integrated design method comprises the steps that a missile longitudinal channel attitude control system model, a longitudinal plane missile-target relative motion model and an all-strapdown seeker longitudinal channel sight decoupling model are built; the state variable and the system output variable are selected, and a guidance and control integrated state space mathematical model considering view field angle constraint is built; a control method combining an obstacle Lyapunov function, an expansion state observer and dynamic surface control is adopted. The control method combining the obstacle Lyapunov function, the expansion state observer and dynamic surface control is adopted, and meanwhile the guidance precision and the all-strapdown seeker view field angle constraint conditions are met, so that it is guaranteed that the body sight angle detected by an all-strapdown seeker in the missile guidance and control process meets the seeker view field constraint.

Description

technical field [0001] The invention relates to a guidance and control integrated design method, in particular to a guidance and control integrated design method considering the field of view constraint of a strapdown seeker. Background technique [0002] With the development of technology, UAV-borne weapons and individual guided weapons are gradually developing in the direction of miniaturization and low cost. Its typical feature is the use of a strapdown system seeker to reduce volume and cost. Ideal for missiles where space is limited. However, the optical axis of the seeker of this type of missile is fixedly connected with the attitude of the missile body, which makes the traditional guidance method based on the angular velocity of the visual line of sight of the inertial missile unable to be used directly, and it is easy to cause the field of view to exceed the limit under the influence of attitude disturbance, resulting in off target. [0003] For the design of the g...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 赵斌周军郭建国冯振欣谭雁英赵辉
Owner NORTHWESTERN POLYTECHNICAL UNIV
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