High Dynamic Rotary Aircraft Composite Guidance Control System and Method

A composite guidance and aircraft technology, applied in control/adjustment systems, attitude control, non-electric variable control, etc., can solve problems such as being unable to meet the requirements of the battlefield environment, the aircraft being susceptible to external interference, reducing the power of the aircraft, and improving the utilization of space. efficiency, reducing misses, and improving flight quality

Active Publication Date: 2022-02-18
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Most of the traditional high-dynamic rotary aircraft are single-guidance systems, which can stably complete the guidance tasks under conventional environmental conditions, but cannot meet the requirements of all-weather, large-span battlefield environments, and the aircraft with single-guidance systems are susceptible to external interference, resulting in guidance The accuracy is reduced, and even cause unfavorable results such as off-target
[0003] In addition, there are many components in the guidance and control cabin of the existing high dynamic aircraft, the structure inside the cabin is complicated, and the volume of the cabin is large, which affects the volume of the warhead and reduces the power of the aircraft.

Method used

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  • High Dynamic Rotary Aircraft Composite Guidance Control System and Method
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  • High Dynamic Rotary Aircraft Composite Guidance Control System and Method

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Embodiment approach

[0085] According to a preferred embodiment of the present invention, the aircraft attitude measurement module 2 is used to obtain the flight parameter information of the aircraft in real time, and transmit it to the steering gear command resolution module 3 .

[0086] In the present invention, the flight parameter information includes roll angle information, pitch angle information and yaw angle information of the aircraft.

[0087] In a further preferred embodiment, the aircraft attitude measurement module 2 includes a geomagnetic sensor 21 and an inertial gyro 22, wherein,

[0088] The geomagnetic sensor 21 is used to obtain the roll angle information of the aircraft in real time,

[0089] The inertial gyroscope 22 is used to obtain pitch angle information and yaw angle information of the aircraft in real time.

[0090] Wherein, the geomagnetic sensor is a magnetoresistive sensor, which works based on the principle that the magnet material has a magnetoresistance effect. I...

Embodiment 1

[0166] The simulation experiment of the aircraft is carried out by computer. The simulation conditions of the highly dynamic rotating aircraft are: the flying speed of the rotating aircraft is 200m / s, the rotational speed is 4πrad / s, and the distance between the aircraft and the target is 10Km;

[0167] The specific simulation guidance control method is as follows:

[0168] (1) According to the distance between the aircraft and the target, select the single-mode guidance mode (radar guidance system);

[0169] (2) The rotating aircraft can be directly simulated by the computer, and the angle of sight between the aircraft and the target, the angle of sight angular velocity between the aircraft and the target, the pitch angle and the yaw angle of the aircraft can be given in real time, where the given The line-of-sight angular velocity between the aircraft and the target is the real value obtained by the seeker of the aircraft, which is sent to the rotating aircraft in real time ...

Embodiment 2

[0190] This embodiment is similar to Embodiment 1, the difference is:

[0191] The distance between the aircraft and the target is 2.99Km;

[0192] In the step (1) of the guidance and control method of concrete simulation:

[0193] According to the distance between the aircraft and the target, select the dual-mode guidance mode (the radar guidance system and the infrared guidance system carry out composite guidance), and the sight angle of the composite guidance is obtained by the following formula (1):

[0194]

[0195] in, Indicates the line-of-sight angle between the aircraft and the target in the compound guidance mode, q 1 Indicates the line-of-sight angle between the aircraft and the target in the guidance mode of the radar guidance system, q 2 Indicates the line-of-sight angle between the aircraft and the target under the guidance mode of the infrared guidance system, a is the weight of the radar guidance system in the compound guidance mode, and b is the weight ...

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Abstract

The invention discloses a compound guidance control system and method for a highly dynamic rotary aircraft, the system comprising a guidance module (1), an aircraft attitude measurement module (2), a steering engine command resolution module (3) and an execution module (4) , wherein, the guidance module adopts a radar / infrared dual-mode composite guidance mode, and automatically switches the guidance mode according to the distance between the aircraft and the target during the flight of the aircraft, which can realize all-weather and multi-environment use, and improves the guidance accuracy; By setting the strapdown seeker and line-of-sight angular velocity calculation module, the space utilization rate of the cabin is improved and the interference is reduced; in addition, the integrated design of the control cabin increases the warhead space and improves the flight quality .

Description

technical field [0001] The invention relates to the field of guidance and control of rotary aircraft, in particular to a compound guidance and control system and method for high dynamic rotary aircraft. Background technique [0002] Most of the traditional high-dynamic rotary aircraft are single-guidance systems, which can stably complete the guidance tasks under conventional environmental conditions, but cannot meet the requirements of all-weather, large-span battlefield environments, and the single-guidance aircraft is susceptible to external interference, resulting in guidance The accuracy is reduced, and even cause unfavorable results such as off-target. [0003] In addition, the guidance and control cabin of the existing high-dynamic aircraft has many components, the structure inside the cabin is complicated, and the volume of the cabin is large, which affects the volume of the warhead and reduces the power of the aircraft. [0004] Therefore, it is necessary to provid...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/0816G05D1/101
Inventor 林德福王雨辰王军波杜少龙王伟
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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