Integrated control method used for semi-strapdown guided missile

A control method, semi-strapdown technology, applied in the field of weapons, can solve the problem of the target leaving the field of view of the seeker, and achieve the effect of reducing conservatism, improving control effect, and improving overall performance

Active Publication Date: 2016-08-17
BEIHANG UNIV +2
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Problems solved by technology

If the response of the semi-strapdown seeker stabilization tracking control system is not timely enough, the missile attitude adjustment under the semi-strapdown system may cause the target to leave the seeker's field of view, especially at the end of the guidance as the relative distance between the missile and the target approaches. This phenomenon is more serious

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  • Integrated control method used for semi-strapdown guided missile
  • Integrated control method used for semi-strapdown guided missile
  • Integrated control method used for semi-strapdown guided missile

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Embodiment Construction

[0024] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0025] The present invention adopts an integrated design method, establishes an integrated model of semi-strapdown seeker and projectile attitude control, and uses nonlinear dynamic inverse control technology to achieve a coordinated control effect between the two sub-systems. The advantages of fast attitude response and small seeker tracking error have guiding significance for the engineering design of the semi-strapdown missile control system.

[0026] The present invention is an integrated control method for semi-strapdown guided missiles, the process is as follows: figure 1 shown, including the following steps:

[0027] Step 1: Establish the integrated mathematical model of seeker stability tracking and projectile attitude control, including projectile attitude kinematics model, frame kinematics model, angle tracking system model, and integrated ...

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Abstract

The invention discloses an integrated control method used for a semi-strapdown guided missile. The method includes the following steps that firstly, missile guider stable tracking and missile body posture control integrated mathematical models are established and include a missile body posture kinematic model, a frame kinematic model, an angle tracking system model and an integrated mathematical model; secondly, an integrated controller configuration is designed; and thirdly, controller design based on non-linear dynamic inverse is conducted. According to the integrated models, the integrated control configuration based on an inner ring and an outer ring is designed, the coupling problem between control loops is solved, the conservative property of design of a control system is reduced, and the comprehensive performance of the system is improved.

Description

technical field [0001] The invention belongs to the fields of weapon technology, seeker technology and control methods, and relates to the design and research of air-to-air missile control systems, in particular to an integrated control method for semi-strapdown guided missiles. Background technique [0002] Seeker stable tracking control is the core technology of semi-strapdown seeker control. In order to study the semi-strapdown stable tracking algorithm, it is necessary to understand the dynamics and kinematics relationship between the missile body and the servo frame, and carry out the semi-strapdown attitude algorithm study in depth. The traditional semi-strapdown seeker stability control system and projectile attitude control system are designed. In order to facilitate the analysis and investigation of the performance of each subsystem, the seeker stability tracking control system and projectile attitude control system are usually regarded as two independent parts. , ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 易科陈建任章李清东晏涛贾晓洪吴军彪周卫文
Owner BEIHANG UNIV
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