Lateral deviation correction method applied to remote guidance aircraft

Abstract

The invention discloses a lateral deviation correction method applied to a remote guidance aircraft. According to the method, an aircraft still can be controlled to connect at a middle end and a tailend on the condition of larger lateral deviation, and a target can enter a field of view of a seeker. The method has the important engineering significance. According to the method, the total range and the real-time lateral deviation distance when the aircraft is started and controlled and the length of the projection of the connecting line between the aircraft and the target on the connecting line between a launching point and a target point are brought into the consideration of a guidance algorithm, and a scientific and reasonable navigation ratio changing in real time is obtained, so that the guidance performance is improved, and the situation that the target enters the field of view range of the seeker when the aircraft is not guided, is guaranteed. In addition, the navigation ratio iscontinuously changed in a small amplitude, and the large-amplitude vibration of a flight path is not caused, so that the stable flight process and the high final hit precision are ensured.

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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