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A Lateral Control Method for One-sided Bomb Landing

A lateral control, unilateral technology, applied in the field of aviation flight control, can solve the problems of difficult to maintain stability and difficult to guarantee landing safety.

Active Publication Date: 2021-08-03
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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  • A Lateral Control Method for One-sided Bomb Landing
  • A Lateral Control Method for One-sided Bomb Landing
  • A Lateral Control Method for One-sided Bomb Landing

Examples

Experimental program
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Effect test

Embodiment 1

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

[0047] Step 1, take out (φ g ) to calculate the integral value in the formula, namely and turn it into the heading alignment segment In the calculation formula, the mode transition process is made smoother and does not trigger (φ g ) limit;

[0048] Step 2, considering that there may be errors in 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 value of 5 consecutive beats at the cut-in moment;

[0049] Step 3. Considering that after the last segment is added, the timeliness of the UAV’s attitude adjustment is poor, the unilateral bomb control strategy is extended from the course alignment section to the straight down section, trajectory flattening section, and course alignment section. In ...

Embodiment 2

[0079] The present invention will be further described now in conjunction with accompanying drawing:

[0080] According to the measurement information of the UAV sensor, p is the roll 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 certain physical quantity), and δ a is the aileron rudder deflection. figure 1 It is the planning diagram of the landing stage of the present invention, which is provided with the flight section of the take-off and landing route, the front section of the straight-line glide section, the rear section of the straight-line glide section, the trajectory flattening section, the course alignment section and the landing roll section.

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

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Abstract

The present invention relates to the field of aviation flight, in particular to a lateral control method for unilateral bomb landing, which comprises the following steps: Step 1, taking out (φ g ) to calculate the integral value in the formula, and transfer it to the calculation formula in the heading alignment segment, and do not trigger (φ g ) limit; step 2, the feedback roll angle is the average value of the current roll angle of the unmanned aerial vehicle for continuous multi-shots at the time of cut-in, and the integral value is also taken as the average value of continuous multi-shots at the time of cut-in; step 3, the unilateral bomb control The strategy extends from the course alignment section to the straight down section, the trajectory leveling section, and the course alignment section, and sets the restriction condition that the cut-in time is a relative altitude of 150m in the straight down section. This application breaks through the limitation of the given limit value of the roll angle, and increases the compensation amount of the lateral asymmetric aileron trim rudder so that the UAV is not affected by the given limit value of the roll angle, so that the original given limit value of the roll angle can still play its original role. Some effect.

Description

technical field [0001] The present invention relates to the technical field of aviation flight control. More specifically, the present invention relates to a single control system applied to the lateral asymmetry of the UAV caused by unilateral bomb landing, unilateral load, and uneven counterweight of the fuselage. A lateral control method for side bomb landing. Background technique [0002] Generally, when the UAV is in combat, it will calculate the missiles currently needed in advance, and then launch into the air. However, it is inevitable that after the target is hit, there are still several missiles hanging on the airframe. In order to ensure the lateral stability of the UAV in the trajectory flattening section and the course alignment section, ordinary UAVs will add a limit to the given value of the roll angle, especially in the course alignment section, the limit will generally be 2 °~3°. When the UAV lands with a bomb on one side, due to the asymmetry of the UAV ...

Claims

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Application Information

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Patent Type & Authority Patents(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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