Aircraft side deviation correction system applied in the area of ​​unstable satellite signal

Abstract

The invention discloses an aircraft side deviation correction system applied to an area where satellite signals are unstable. The system includes a quasi-satellite guidance calculation module, a microprocessor module and a navigation ratio output module. The quasi-satellite guidance calculation module is used for When the star is lost, the microprocessor module is provided with the aircraft position and speed information required by the overload at the present moment for calculating the side deviation; the navigation ratio of the real-time change is provided for the microprocessor module by the navigation ratio output module, and the navigation ratio output is The module obtains the real-time changing navigation ratio according to the total range, real-time lateral distance and other information when the aircraft is controlled, 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 large vibrations in the flight path, ensuring a stable flight process and high final hit accuracy.

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 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 en...

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 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, it will naturally be unable to guide, 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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