Singularity processing method of terminal maneuver small-overload guidance command

A technology of guidance instructions and processing methods, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., to avoid meaningless attitude maneuvers, avoid singular problems, and reduce the effect of large-scale projectile roll

Inactive Publication Date: 2016-10-12
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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  • Application Information

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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

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  • Singularity processing method of terminal maneuver small-overload guidance command
  • Singularity processing method of terminal maneuver small-overload guidance command
  • Singularity processing method of terminal maneuver small-overload guidance command

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Embodiment Construction

[0019] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.

[0020] This embodiment provides a singular processing method for terminal maneuver and small-overload guidance commands, which is suitable for lift-type aircraft that mainly fly with aerodynamic force.

[0021] figure 1 It is a schematic flow chart of the singular processing method of the terminal maneuvering small overload guidance instruction in the embodiment of the present invention. Such as figure 1 As shown, the singular processing method of the terminal maneuvering small overload guidance instruction in the embodiment of the present invention includes:

[0022] Step 101, according to the preset guidance law and scheme of the terminal maneuvering section, calculate the longitudinal guidance force F ycx and lateral guidance force F zcx .

[00...

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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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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 黄万伟马卫华杨业祁振强包为民梁禄扬吴浩郭涛徐国强唐海红
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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