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Aircraft guidance system and method for realizing fall angle constraint

A technology of guidance system and aircraft, which is applied in the field of aircraft guidance, can solve the problems that the aircraft cannot be restricted by the falling angle, and the attack target cannot be achieved, so as to achieve the effect of flexible use and improved damage capability

Active Publication Date: 2021-10-12
BEIJING INSTITUTE OF TECHNOLOGYGY +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] When the traditional guidance aircraft intercepts the target, its proportional guidance form is relatively simple. When it is necessary to specify the position of the target, especially when it is necessary to attack the weakest position of the target, such as the top, the aircraft is usually required to be able to fly with a larger landing speed. At this time, the traditional proportional guidance form cannot realize the constraint of the falling angle of the aircraft, and thus cannot attack the weak position of the target with a larger falling angle

Method used

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  • Aircraft guidance system and method for realizing fall angle constraint
  • Aircraft guidance system and method for realizing fall angle constraint
  • Aircraft guidance system and method for realizing fall angle constraint

Examples

Experimental program
Comparison scheme
Effect test

experiment example 1

[0119] Select the flight type model that can realize the fall angle constraint, the aircraft is equipped with the aircraft guidance system of the fall angle constraint, the system includes that the guidance system includes the projectile visual line of sight angle measurement module, the guidance law solution module and the execution module, the projectile goal The line of sight angle measurement module is used to measure the sight line angle of the aircraft in real time,

[0120] After the aircraft is started and controlled, the guidance law calculation module calculates the guidance law in real time according to the measured projectile sight angle, and the execution module can control the movement of the aircraft according to the guidance law information calculated by the solution.

[0121] Wherein, the guidance law solving module can obtain the guidance law by solving the following formula (1):

[0122]

[0123] In the formula, B=-w|s| 1 / 2 sgn(s)+ξ,

[0124] Among th...

experiment example 2

[0148] Select the flight type model that can realize the fall angle constraint. The aircraft is installed with the same aircraft guidance system with the fall angle constraint as in Experimental Example 1. module, the bullet eye sight angle measurement module is used to measure the bullet eye sight angle of the aircraft in real time,

[0149] After the aircraft is started and controlled, the guidance law calculation module calculates the guidance law in real time according to the measured projectile sight angle, and the execution module can control the movement of the aircraft according to the guidance law information calculated by the solution.

[0150] In this experiment, with r=5000m, V m =300m / s, aircraft starting coordinate X M = 0m, Y M =0m; fixed target coordinate X T =1000m, Y T = 0m for ballistic simulation, where the falling angles of the aircraft are respectively 30°, 45°, 60°, 90°, and 105°, the launch angle of the aircraft can be calculated through the above f...

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Abstract

The invention discloses an aircraft guidance system and method for realizing fall angle constraint. The system can firstly set a launching angle of an aircraft by inputting an expected fall angle and a target distance coordinate; a missile-target sight angle of the aircraft in real time is measured through a missile-target sight angle measuring module after the aircraft is started and controlled, and the measured missile-target sight angle is transmitted to a guidance law resolving module in real time; the guidance law resolving module is used for resolving a guidance law in real time according to the measured missile-target sight angle after the aircraft is started and controlled, and transmitting the resolved guidance law information to an execution module in real time; and the execution module can control the aircraft to move according to the calculated guidance law information, so that the falling angle constraint of the aircraft is realized.

Description

technical field [0001] The invention relates to the technical field of aircraft guidance, in particular to an aircraft guidance system and method for realizing fall angle constraints. Background technique [0002] When the traditional guidance aircraft intercepts the target, its proportional guidance form is relatively simple. When it is necessary to specify the position of the target, especially when it is necessary to attack the weakest position of the target, such as the top, the aircraft is usually required to be able to fly with a larger landing speed. At this time, the traditional proportional guidance form cannot realize the constraint on the falling angle of the aircraft, and thus cannot attack the weak position of the target with a larger falling angle. [0003] Therefore, based on the above-mentioned problems, it is urgent to design a guidance system and method that can realize the constraint of the aircraft fall angle. Contents of the invention [0004] In orde...

Claims

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Application Information

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IPC IPC(8): F42B15/01F41G3/00F41G7/34
CPCF42B15/01F41G3/00F41G7/343
Inventor 王伟刘佳琪胡宽容王伟斌王录强南宇翔
Owner BEIJING INSTITUTE OF TECHNOLOGYGY