Minimum overload terminal guiding method with terminal angular constraint

Abstract

The invention discloses a minimum overload terminal guiding method with terminal angular constraint. By using the method, the minimum theoretical value of a required overload under an ideal system can be obtained, and large terminal angle high-precision terminal guidance is obtained on the premise of being close to the minimum ideal required overload as far as possible. According to the content, the method comprises the steps that firstly, a circular-linear guidance law uCLGL(t) is calculated for the ideal system according to a target position and the terminal angular constraint, so that the lower limit of the required overload under the large terminal angle is determined, and the design is used for guiding a guided weapon to achieve the maneuvering capability required by the large terminal angle; secondly, according to a non-ideal system with lagged links of an automatic pilot, the tail of the circular-linear guidance law is switched into a polynomial guidance law with first-order derivative compensation, so that the combined guidance law is formed, the switching condition is given, the required overload behind the switching point is not larger than the required overload in front of the switching point, and meanwhile terminal position and angular errors can be effectively reduced.

Description

technical field [0001] The invention relates to the technical field of the terminal guidance method of guided weapons, in particular to a minimum overload terminal guidance method with fall angle constraints. Background technique [0002] In order to improve the effectiveness of terminal damage, in addition to requiring high hit accuracy, guided weapons have also gradually increased the requirements for the attitude of the missile at the hit point in recent years. For example, for guided bombs filled with preset fragments, it is usually hoped that the missile body will fall vertically into the target area so that the damage effect of the preset fragments can be fully exerted; The angle requirements are more decisive, because in the case of small falling angles, the guided rockets can easily slip on the hard target surface and cause ricochets, so that the warhead cannot penetrate the target body, and the attack effectiveness is completely lost; even if it can penetrate the ta...

AI Technical Summary

Problems solved by technology

However, for the guided rockets with canard control, the change law of its flight speed is gradually attenuating, and the terminal flight speed will be attenuated to about 30% to 50% of the end of its active section (the point of maximum speed); at the same time, its restoring torque (The moment that reduces the manoeuvrability of the projectile body) Due to the large increase in the reduction of speed, the above characteristics lead to low maneuverability at the end of the guided rocket, and it is generally difficult to have sufficient rapid downward maneuverability

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