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Spoiler system provided on a guided aircraft and method of applying same

A technology for spoilers and aircraft, applied in the field of spoiler systems, can solve problems such as reduced hit accuracy, disordered aircraft force, increased projectile jitter, etc. Effect

Active Publication Date: 2020-12-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the solutions in the prior art also have many shortcomings. For example, if the drag plate is too large or continuously deployed, it will have a negative impact on the long-range maneuverability of the aircraft; in addition, for the rolling guided aircraft, the drag plate It is also difficult to control the deployment timing and deployment time, which is very likely to cause the aircraft to be disturbed by force, increase the vibration of the projectile body, and reduce the final hit accuracy.

Method used

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  • Spoiler system provided on a guided aircraft and method of applying same
  • Spoiler system provided on a guided aircraft and method of applying same
  • Spoiler system provided on a guided aircraft and method of applying same

Examples

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Effect test

experiment example 1

[0113] Experimental Example 1, when the guided aircraft is not equipped with the spoiler system described in this application, it strikes a target at a distance of 18km, and the ballistic trajectory obtained is as follows: Figure 4 As shown in the middle solid line, set the target to strike at 20km. Since the power design of the aircraft is not enough to hit the target at 20km, the final ballistic trajectory is as follows: Figure 5 shown by the solid line;

experiment example 2

[0114] Experimental example 2, after the spoiler system described in the application is installed on the guided aircraft, the target at a distance of 18km is attacked, and this spoiler also starts working at this time, and the ballistic trajectory obtained is as follows Figure 4 As shown by the dotted line in the middle, set the target at 20km to strike. Since the spoiler system is installed in the aircraft, it can finally hit the target, and the final trajectory obtained is as follows: Figure 5 shown by the dotted line;

[0115] From the comparison of the above-mentioned Experimental Example 1 and Experimental Example 2, it can be seen that the spoiler system provided by the present invention can effectively increase the range of the aircraft without reducing the hit accuracy.

experiment example 3

[0116] Experimental Example 3, when the guided aircraft is not equipped with the spoiler system described in this application, it strikes a target at a distance of 16km, and the amount of lateral deviation after the start of control is about 1100 meters, and its ballistic correction trajectory is as follows: Figure 6 As shown by the solid line,

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PUM

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Abstract

The invention discloses a spoiler system arranged on a guidance aircraft and a method applying the system. The system comprises a spoiler arranged inside the tail of the aircraft, and the spoiler canstretch out of or draw back into the aircraft; when the spoiler stretches out of the aircraft, the flight attitude of the aircraft can be changed; since the aircraft continuously rotates in the running process, therefore the orientation of the spoiler on the aircraft is changed in real time; by adjusting the time for the spoiler to stretch out, different acting forces and moments can be provided for the aircraft through the spoiler, and when the spoiler is located above the aircraft and stretches out, acting force for the front end of the aircraft to life can be provided; when the spoiler is located at the left side of the aircraft and stretches out, acting force for making the front end of the aircraft skew to the left can be provided.

Description

technical field [0001] The invention relates to a control system and method for a guided aircraft, in particular to a spoiler system arranged on a guided aircraft and a method for applying it. Background technique [0002] The guidance of the guided aircraft is driven by changing its own aerodynamic force, such as drag rings, drag plates, canards, etc. are all aerodynamically controlled actuators. Through the change of aerodynamic force, the guided aircraft can achieve some established goals. Under high overload conditions, the maneuverability of the aircraft can also be further improved. [0003] In the prior art, the resistance and lateral force are adjusted by opening the resistance plate at a suitable position, so as to achieve the purpose of adjusting the landing point. [0004] However, the solutions in the prior art also have many shortcomings. For example, if the drag plate is too large or continuously deployed, it will have a negative impact on the long-range mane...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C5/12
Inventor 王伟刘佳琪程文伯林德福王江王辉陈柏霖林时尧纪毅师兴伟裴培唐攀李虹言
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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