A Singular Processing Method of Terminal Maneuvering Small Overload Guidance Command

Abstract

The invention discloses a singularity processing method of a terminal maneuver small-overload guidance command. The method comprises the steps of calculating to obtain a longitudinal guidance force Fycx and a horizontal guidance force Fzcx according to a preset terminal maneuver phase guidance law and scheme; performing singularity processing on the guidance force: if Kc*m*g0 is greater than Fycx, Fyn=sign(Kc*m*g0)*|Kc*m*g0|, otherwise, Fyn=Fycx; calculating an angle of heel required by guidance according to the guidance force after the singularity processing; and calculating a normal force required by guidance according to the longitudinal guidance force Fycx and the horizontal guidance force Fzcx. The method provided by the invention can solve the problem of singularity an aircraft with a high lift-to-drag ratio in a terminal maneuver flight phase caused by a small-overload guidance command, reduces unnecessary large-amplitude missile body roll, and improves the guidance accuracy.

Description

technical field [0001] The invention relates to the technical field of hypersonic vehicle guidance, in particular to a singular processing method for terminal maneuver small overload guidance commands. Background technique [0002] Due to the large lift force of the lift-type hypersonic vehicle, when the vehicle is close to the target, it is very easy to have a small overload guidance command when the vehicle is flying in the terminal maneuvering segment. At this time, the longitudinal and lateral guidance force requirements given by the guidance law are relatively small. Longitudinal guidance forces may occur | F ycx |≤0.1g 0 , lateral guidance force|F zcx |≤0.1g 0 In the case of , at this time, if still according to γ cx =tg -1 (F zcx / F ycx ) to calculate the roll angle command γ cx , will lead to a large roll angle, even to 90°, which is particularly unfavorable for attitude control and guidance. [0003] The tilt caused by the small overload guidance command is...

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Problems solved by technology

[0005] In view of this, the present invention provides a singularity processing method for terminal maneuvering and small overload guidance commands, which can solve the singular problem caused by small overload guidance commands in the terminal maneuvering flight segment of high-lift-to-drag ratio aircraft, and reduce unnecessary large-scale projectile roll. Turn, improve guidance accuracy

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