A method of yaw correction applied to long-distance guided aircraft

Abstract

The invention discloses a side deviation correction method applied to a long-distance guided aircraft. The method can enable the aircraft to control the aircraft to enter the field of view of the seeker when the aircraft is handed over in the middle and the end when the side deviation is large. , which is of great engineering significance; this method takes into consideration the guidance algorithm the total range of the aircraft when it starts to control, the real-time yaw distance, and the projected length of the line between the aircraft and the target on the line between the launch point and the target point, and obtains Scientific and reasonable real-time changing navigation ratio, so as to improve its guidance performance and ensure that the target enters the field of view of the seeker when it enters the terminal guidance. In addition, since the navigation ratio changes continuously in a small range, it will not cause The large-scale vibration of the flight path ensures a smooth flight process and high accuracy of the final hit.

Description

technical field [0001] The invention relates to the field of guidance and control of long-distance guided aircraft, in particular to a side deviation correction method applied to long-distance guided aircraft. Background technique [0002] For long-distance guided aircraft, in order to increase its range, various measures are often used in the climb section of the flight trajectory to make the aircraft climb higher, such as rocket range extension, bottom row technology, or the use of high-power gunpowder, etc., but these measures are often prolonged. The flight time of the aircraft's climb section is limited, which makes the aircraft's start-up time generally set after 50s after launch. However, the long flight time before the start of control makes the aircraft unable to control its flight to the target along the expected trajectory during this period, coupled with the influence of crosswind, Magnus force generated by its own rotation, and interference at the launch end, I...

AI Technical Summary

Problems solved by technology

[0002] For long-distance guided aircraft, in order to increase its range, various measures are often used in the climb section of the flight trajectory to make the aircraft climb higher, such as rocket range extension, bottom row technology, or the use of high-power gunpowder, etc., but these measures are often prolonged. The flight time of the aircraft's climbing section is limited, which makes the aircraft's start-up time generally set after 50s after launch.

However, the long flight time before the start of control makes the aircraft unable to control its flight to the target along the expected trajectory during this period, coupled with the influence of crosswind, Magnus force generated by its own rotation, and interference at the launch end, It often forces the aircraft to have a large sideways distance when starting the control, and even if the general lateral guidance method can control the aircraft to fly to the target, when it enters the final guidance section, it is often difficult to control the aircraft to make the target enter. The field of view of the seeker, the general criterion for entering the field of view is: when the distance from the target is 3km, the side deviation is less than 600m

[0003] If the aircraft fails to make the target enter the field of view of the seeker when it enters the final guidance section, it will be difficult for the aircraft to capture the target in the final guidance section, and will eventually miss the target with a high probability;

[0004] In addition, in the guidance and control process of the aircraft, if different guidance laws are used for different stages, it will inevitably cause large vibrations in the flight path of the aircraft and reduce the stability of the aircraft;

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