A Longitudinal Guidance Method for the Glide Flight Section of Hypersonic Vehicle

Abstract

The invention discloses a longitudinal guidance method for the gliding flight section of a hypersonic flight vehicle. The method includes the steps that in the gliding section flight process, a guidance system generates a standard flight path instruction in real time according to navigation parameters; the guidance system provides a preset attack angle acx0 according to the flight speed or Mach in the standard flight path instruction; an additional attack angle instruction Dacx is calculated according to the path instruction and measured values provided by a navigation system; a current actual attack angle acx is acquired through calculation according to the preset attack angle acx0 and the additional attack angle instruction Dacx. By the adoption of the longitudinal guidance method for the gliding flight section of the hypersonic flight vehicle, the dynamic characteristic of drag acceleration tracking control can be effectively improved, the tracking control accuracy of drag acceleration under the dynamic condition is improved, fluctuation of a flight path is restrained, and the adaptability of the guidance system to deviations, uncertain interference and uncertain conditions is enhanced.

Description

technical field [0001] The invention relates to hypersonic vehicle navigation, guidance and control technology, in particular to a longitudinal guidance method for the gliding flight section of a hypersonic vehicle. Background technique [0002] In the prior art, for gliding vehicles with high lift-to-drag ratio characteristics, most of them fly with preset angles of attack during their hypersonic flight segment, and do not make any adjustments to their flight angles of attack. When the aircraft rolls over, due to the limitation of the rolling angular rate, the angular rate is generally less than 20° / s. Therefore, if the rollover operation is performed from a negative 60-degree roll angle to a positive 60-degree roll angle, it generally takes at least 6 seconds The time is even more than 10 seconds under deviation conditions, so it will have an adverse effect on the resistance acceleration tracking guidance, resulting in a large error in the resistance acceleration tracking ...

AI Technical Summary

Problems solved by technology

When the aircraft rolls over, due to the limitation of the rolling angular rate, the angular rate is generally less than 20° / s. Therefore, if the rollover operation is performed from a negative 60-degree roll angle to a positive 60-degree roll angle, it generally takes at least 6 seconds Under deviation conditions, it will even exceed 10 seconds, so it will have an adverse effect on the resistance acceleration tracking guidance, resulting in a large error in the resistance acceleration tracking under dynamic conditions

In addition, since the aircraft's angle of attack does not make any adjustments, when the aircraft rolls over, it will also cause fluctuations in the flying height and ballistic inclination of the gliding aircraft, which will have an adverse effect on guidance

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