Aircraft lateral deviation correction system applied to unstable satellite signal area

Abstract

The invention discloses an aircraft lateral deviation correction system applied to a satellite signal unstable area. The system comprises a pseudo-satellite guidance resolving module, a microprocessormodule and a navigation ratio output module. The pseudo-satellite guidance resolving module is used for providing aircraft position and speed information at the current moment required for calculating overload required by lateral deviation for the microprocessor module when a satellite is lost; the navigation ratio output module is used for providing a navigation ratio changing in real time for the microprocessor module; the navigation ratio output module obtains a navigation ratio changing in real time according to the total range and the real-time lateral deviation distance when the aircraft is started and controlled and other information. Therefore, the guidance performance is improved, a target can enter the field of view range of the seeker when entering terminal guidance. In addition, since the navigation ratio is continuously changed at a small amplitude, large-amplitude vibration of the flight path cannot be caused, flight process is stable, and the final hit precision is high.

Description

technical field [0001] The invention relates to the field of guidance and control of aircraft, in particular to an aircraft lateral deviation correction system applied to areas where satellite signals are unstable. 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 often extend 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, It of...

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 often extend 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 and system can control the aircraft to fly to the target, when entering the terminal guidance section, the general lateral guidance method and system are often difficult to control The aircraft makes the target enter the field of view of the seeker, and the general criterion for entering the field of view is: when the distance from the target is 3km, the lateral deviation is less than 600m

[0003] In addition, during the traveling process of the aircraft, it is very likely to be interfered by signals on some road sections, and the satellite signals cannot be received clearly and in contact, and the entire guidance and control process relies on the basic information provided by satellite signals. As far as the guided aircraft is concerned, the phenomenon of star loss is more serious. Before the final guidance stage, if the satellite signal is lost, the guidance will naturally be impossible, and its lateral deviation may be even greater;

[0004] 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; The use of guidance laws with large differences will inevitably cause large vibrations in the flight path of the aircraft and reduce the stability of the aircraft;

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