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Suboptimal guidance method with terminal angle constraint

A sub-optimal technology with end angle constraints, applied in the field of guidance, can solve problems such as inaccurate measurement

Inactive Publication Date: 2014-01-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, this method can only strike stationary targets, but is powerless against moving targets
In addition, the method applies a variable of remaining flight time, which cannot be accurately measured in current practice

Method used

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  • Suboptimal guidance method with terminal angle constraint
  • Suboptimal guidance method with terminal angle constraint
  • Suboptimal guidance method with terminal angle constraint

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Embodiment Construction

[0103] In order to better illustrate the purpose and advantages of the present invention, the technical solution will be further described in detail below in conjunction with the accompanying drawings and examples.

[0104] 1. Guidance law design with end angle constraints

[0105] A lift-type reentry vehicle is used as an example to introduce the method. The mass of the vehicle is 1000kg, and the reference area is 2.5m 2 . The coordinates of the starting position of the aircraft (x 0 ,y 0 ) is (0, 30)km, the initial ballistic inclination is -3deg, and the initial velocity is 1500m / s. Target starting position coordinates (x f0 ,y f ) is (100,0)km, the target speed is horizontal 20m / s, and the terminal ballistic inclination is -60deg. Other simulation parameters that need to be used are selected as follows:

[0106] N=10, ζ=1e6.

[0107] Step 1, establish the kinematics and dynamics model of the two-dimensional plane aircraft:

[0108] x ...

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Abstract

The invention relates to a suboptimal guidance method with terminal angle constraint, and belongs to the field of guidance technologies. The suboptimal guidance method has six advantages that influence, on the guidance process, of aerodynamic characteristics (aerodynamic resistance and the gravity) of an air vehicle is considered, so that the method is closer to a practical situation; people only need to know initial conditions and tail end requirements of a flight and real-time state information of the air vehicle to achieve terminal guidance, and therefore the amount of needed information is small; an obtainable trajectory inclination angle terminal value is wide in range; an obtained controlled quantity is smooth in variation and is easy for an attitude control system to track; a weight matrix Q is the function based on a residual height y-to-go (or a residual firing range x-to-go), and the quantities are easy to measure in a project; not only can an object be hit with an expected terminal angle, but also a constant value speed object can be hit with an expected attitude.

Description

technical field [0001] The invention relates to a suboptimal guidance method with end angle constraints, which belongs to the technical field of guidance. Background technique [0002] In the field of modern guidance, since the terminal collision angle is closely related to the actual strong damage effect, for the terminal guidance section, not only the minimum miss amount at the terminal point is required, but also the desired terminal angle constraint must be satisfied. [0003] The concept of guidance with end angle constraints was proposed by Kim and Grider in 1973. Since then, a large number of researchers at home and abroad have conducted in-depth research in this field. Due to its simple form and easy engineering application, proportional guidance is widely used in the design of guidance laws with end angle constraints. Kim et al. proposed a biased proportional guidance method, which obtained the desired end angle by adding a time-varying term to the proportional gu...

Claims

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Application Information

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IPC IPC(8): F41G3/00
Inventor 盛永智赵曜刘向东
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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