Aircraft guidance control system

Abstract

The invention discloses an aircraft guidance control system. The system comprises a quasi-satellite guidance resolving module, a microprocessor module and a virtual target simulation module, wherein the quasi-satellite guidance resolving module is used for providing aircraft position and speed information at the current moment for the microprocessor module when a satellite is lost; the microprocessor module is used for calculating required overload, the required overload comprises the required laterodeviation overload for correcting the laterodeviation of the aircraft, and the required laterodeviation overload is obtained by multiplying a navigation ratio, the flight speed of the aircraft and the missile-to-target line-of-sight angular rate in the laterodeviation direction; and the virtualtarget simulation module is used for giving the position of a virtual target point in real time according to the flight time after starting control and then calculating the missile-to-target line-of-sight angular rate in the laterodeviation direction according to the position of the aircraft and the position of the virtual target point so as to obtain the required overload capable of correcting laterodeviation. Thereby, the aircraft is guided and controlled accordingly, and the aircraft flies towards the target under the condition of correcting laterodeviation.

Description

technical field [0001] The invention relates to the field of guidance and control of aircraft, in particular to a guidance and control system capable of guiding and controlling the aircraft under the condition of staged star loss and large lateral deviation. 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...

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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