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A Multi-missile Cooperative Guidance Method with Finite Time Convergence

A time-limited, multi-missile technology, applied in directional control systems, offensive equipment, weapon accessories, etc., can solve problems such as the inability to guarantee the limited-time convergence characteristics of the cooperative guidance law, and the inability to control the collision angle, so as to meet the rapidity of the battlefield. Requirements and realization of the effect of collision angle control

Active Publication Date: 2022-07-22
NANJING UNIV OF SCI & TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although the above method can achieve multi-missile saturation attack, it cannot realize the control of the collision angle, and cannot guarantee the finite time convergence characteristics of the cooperative guidance law, and rapidity is an important requirement on the battlefield

Method used

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  • A Multi-missile Cooperative Guidance Method with Finite Time Convergence
  • A Multi-missile Cooperative Guidance Method with Finite Time Convergence
  • A Multi-missile Cooperative Guidance Method with Finite Time Convergence

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Embodiment

[0098] This embodiment uses a proposed distributed cooperative guidance method with collision angle control to design a cooperative guidance simulation experiment. The parameters related to the communication topology are set as: a 12 =a 21 =1,a 13 =a 31 =0,a 14 =a 41 =0,a 23 =a 32 =1, a 24 =a 42 =0,a 43 =a 34 =1. The control parameters are designed as: M i =120,p i =9,q i =7,β i =9,N=3,k 1i =k 2i =k 3i = 124. The initial conditions are given in Table 1.

[0099] Table 1

[0100]

[0101] figure 2 It is the trajectory map of the remaining flight distance of the missile during the simulation process. from figure 2 It can be seen that all missiles end guidance at the same time.

[0102] image 3 It is the flight trajectory diagram of the missile during the simulation process. from image 3 It can be seen that all missiles can successfully hit the target, and the combination figure 2 It is known that all missiles hit the target at the same time.

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Abstract

The invention discloses a multi-missile cooperative guidance method with limited time convergence. The method is: firstly establish the relative kinematics model of the projectile; then measure and update the motion parameters; then estimate the remaining flight time; then obtain the remaining flight time of other missiles through the communication link, and calculate the relative synchronization error; then calculate the time-varying navigation ratio Then calculate the tangential acceleration command; then design the terminal angle control term; then calculate the normal acceleration command; finally input the guidance command to the actuator to control the missile flight; repeat the motion parameter measurement and update and cooperative guidance control until the guidance Finish. The invention has the characteristic of limited time convergence and can realize the control of the collision angle, thereby enhancing the damage capability of the missile.

Description

technical field [0001] The invention relates to the technical field of missile guidance, in particular to a multi-missile cooperative guidance method with limited time convergence. Background technique [0002] Modern warships are usually equipped with powerful missile defense systems, such as close-in defense systems. These weapons can easily destroy missiles based on conventional technology. Therefore, advanced guidance technologies such as angle control guidance and cooperative guidance are becoming the current research hotspots. Among them, coordinated guidance can achieve saturation attack, making it an effective strategy to deal with shipboard defense systems. I.S Jeon (I.S Jeon, J.I.Lee and M.J.Tahk, Homing GuidanceLaw for Cooperative Attack of Multiple Missiles,"Journal of Guidance,Control andDynamics,vol.33,no.1,pp.275-280,May,2012) proposed based on proportional navigation A cooperative guidance method is proposed, which utilizes a time-varying navigation scale ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F41G7/30
CPCF41G7/308
Inventor 易文俊张文广
Owner NANJING UNIV OF SCI & TECH
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