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Auto-rotation gliding control method of unmanned helicopter

A technology of unmanned helicopter and control method, which is applied in the field of flight control, and can solve the problems that the research of unmanned helicopter autorotation and glide has not been reported.

Inactive Publication Date: 2017-06-20
FLIGHT AUTOMATIC CONTROL RES INST
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AI Technical Summary

Problems solved by technology

[0003] In China, only a few autorotation and descent flight tests have been done on a certain type of manned helicopter, and there is no domestic report on the autorotation and descent of unmanned helicopters.

Method used

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  • Auto-rotation gliding control method of unmanned helicopter
  • Auto-rotation gliding control method of unmanned helicopter
  • Auto-rotation gliding control method of unmanned helicopter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0028] 1. Autorotation slide control method for engine failure

[0029] Design the flight profile of autorotation glide as follows: figure 1 , the overview of the autorotation glide flight process is shown in Table 1.

[0030] Table 1 Rotation and glide flight stages

[0031]

[0032] The simulation data curve of autorotation slide when the engine fails is as follows: figure 2 .

[0033] 1.1. Stable rotation section

[0034] Analyze the relationship between forward flight speed and descent rate during autorotation glide. The basic law is: maintaining a certain forward flight speed can minimize the rate of descent, and too high or too small forward flight speed will increase the rate of descent. Finalize the forward flight speed and descent rate commands for stable autorotation flight.

[0035] Therefore, when entering the autorotation descent, quickly reduce the collective pitch to the minimum, and at the same time enter the vertical speed holding mode and the airspe...

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Abstract

The invention relates to an auto-rotation gliding control method of an unmanned helicopter. The method includes design of an auto-rotation gliding flight section, design of a flight control law and simulation verification in a condition with engine failure and scull failure of the unmanned helicopter. According to the invention, control of safe landing of the unmanned helicopter is simulated in the condition with engine failure and scull failure. Through analyzing the auto-rotation flight feature of the unmanned helicopter, the flight section in an engine failure state is designed and a motion command is generated. By adopting a classic control method, control law parameter regulation is performed according to the auto-rotation flight features and accurate tracking of the motion command is realized. The method is tested and verified in a simulation environment. The landing state meets safety requirements and the validity of the control method is proved.

Description

technical field [0001] The invention relates to a self-rotation and glide control method of an unmanned helicopter, which belongs to the technical field of flight control. Background technique [0002] Helicopter autorotation and glide flight refers to emergency control of the helicopter after engine failure or tail rotor failure during flight, making full use of the conversion between kinetic energy and gravitational potential energy, so that the helicopter enters the autorotation and glide state stably, and finally realizes safety. The process of landing. Autorotation performance is an important indicator of helicopter design, especially for single-engine helicopters, the quality of autorotation performance is more important. [0003] In China, only a few autorotation and descent flight tests have been done on a certain type of manned helicopter, and there is no domestic report on the research on the autorotation and descent of unmanned helicopters. Contents of the inve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
CPCG05D1/102
Inventor 王冬赵建伟禹科王琳董强
Owner FLIGHT AUTOMATIC CONTROL RES INST
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