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Transverse control method of single-side missile hanging landing

A laterally controlled, unilateral technique

Active Publication Date: 2019-08-06
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the asymmetry is large and the required roll angle setting value is greater than its limit, it will be difficult for the UAV to maintain lateral stability and landing safety is difficult to guarantee

Method used

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  • Transverse control method of single-side missile hanging landing
  • Transverse control method of single-side missile hanging landing
  • Transverse control method of single-side missile hanging landing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0046] A lateral control method for unilateral hanging bomb landing, characterized in that it comprises the following steps:

[0047] Step 1, take out (φ) before turning into the course alignment section g ) to calculate the integral value in the formula, that is and turn it into the heading alignment segment In the calculation formula, the modal transition process is made smoother without triggering (φ g );

[0048] Step 2, considering that there may be errors in the data of a single shot in the real-time calculation, the feedback roll angle is the average value of the current roll angle of the drone for 5 consecutive shots at the cut-in time. The integral value also takes the average of 5 consecutive beats at the cut-in time;

[0049] Step 3, considering that after the last stage is added, the UAV's attitude adjustment is less efficient, extend the unilateral bomb control strategy from the course alignment section to the straight-line glide section, the trajectory lev...

Embodiment 2

[0079] Now in conjunction with the accompanying drawings, the present invention will be further described:

[0080] According to the measurement information of the UAV sensor, p is the roll angle rate, φ is the roll angle, is the side offset speed, Y is the side offset distance, ψ k is the track angle, the subscript g represents the given target value of the physical quantity (hereinafter referred to as the given value of a physical quantity), δ a Aileron rudder offset. figure 1 It is a planning diagram of the landing stage of the present invention, which includes a take-off and landing route flight section, a front section of a straight-line glide section, a rear section of the straight-line glide section, a trajectory leveling section, a course alignment section, and a landing roll section.

[0081] 1. According to the laterally asymmetric UAV landing characteristics caused by unilateral hanging bombs, in the control law design, the design ideas of the control law to real...

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Abstract

The invention relates to a transverse control method of single-side missile hanging landing, and belongs to the field of aviation flight. The method comprises the following steps that 1) an integral quantity is taken from a (phi<g>) calculation formula (delta) before a course aligning phase is turned to, and turned into a calculation formula in the course aligning phase, and the amplitude ofthe (phi<g>) is not triggered; 2) a mean value of the present roller angle of a UAV in multiple continuous beats during cut-in is taken as the feedback roll angle, and a mean value of multiple continuous beats during cut-in is taken as the integral quantity; and 3) a single-side missile hanging control strategy is widened from only the course aligning phase to linear downslide, trajectory flareout and course aligning phases, and the limit of the relative height of 150m during cut-in is set for the trajectory flareout phase. The roll angle is not limited to a given limit value, a transverse asymmetric aileron tromming tab compensation quantity is added to avoid the UAV from influence of the given roll angle limit value, and the original given roll angle limit value can play original roles.

Description

technical field [0001] The invention relates to the technical field of aeronautical flight control, and more particularly, the invention relates to a unilateral asymmetrical unit applied to the unmanned aerial vehicle due to unilateral hanging bomb landing, unilateral hanging load, uneven fuselage counterweight, etc. Lateral control method of side-mounted bomb landing. Background technique [0002] Generally, when the UAV is in combat, it will calculate the currently required missiles in advance before launching into the air. However, it is inevitable that after the target is hit, there are still several missiles left hanging on the body. In order to ensure the lateral stability of the UAV in the trajectory leveling section and the heading alignment section, ordinary UAVs will increase the limit on the given value of the roll angle, especially the heading alignment section, the limit will generally be 2 °~3°. When the UAV unilaterally hangs the bomb and lands, due to the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10G05D1/08
CPCG05D1/0816G05D1/101
Inventor 金波王庆琥熊维康
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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