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Optical cable laying based coaxial double-rotor-wing unmanned helicopter parameter identification test system

A coaxial dual-rotor, unmanned helicopter technology, applied in the aviation field, can solve problems such as complex modeling methods

Active Publication Date: 2015-03-04
SHENZHEN MINGXIN AVIATION TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The coaxial twin-rotor unmanned helicopter is very suitable for the rapid laying of flexible cables such as optical cables due to its unique layout. The influence of the drag-type flexible optical cable on the dynamic characteristics of the aircraft, so its modeling method is more complicated

Method used

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  • Optical cable laying based coaxial double-rotor-wing unmanned helicopter parameter identification test system
  • Optical cable laying based coaxial double-rotor-wing unmanned helicopter parameter identification test system
  • Optical cable laying based coaxial double-rotor-wing unmanned helicopter parameter identification test system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0128] Embodiment 1: as Figure 3-5 As shown, the control-oriented coaxial dual-rotor unmanned helicopter platform dynamics model for laying optical cables is established first, and the process is as follows:

[0129] The helicopter motion can be expressed as the following vector equation:

[0130] x . = f ( x , u ) , - - - ( 3.17 )

[0131] Here x is the state vector of the helicopter, That is, the derivative of x in the mathematical sense, u is the control input variable of the helicopter, here x=[u, v, w, φ, θ, ψ, p, q, r], and the meanings represented by each parameter are: roll Rotation rate p, pitch rate q, yaw rate r, roll angle φ, pitch angle θ, heading angle ψ, forward velocity u, lateral velocity v, vertical velocity w. u is the control inpu...

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Abstract

An optical cable laying based coaxial double-rotor-wing unmanned helicopter parameter identification test system comprises an aircraft platform and a ground device; an inertia measuring unit, a global positioning system, a magnetic heading meter, a laser height indicator, a data recorder and a controller are respectively installed on the aircraft platform; the inertia measuring unit, the global positioning system, the magnetic heading meter, the laser height indicator and the data recorder are connected to the controller; the controller processes signals and outputs the signals to the control unit; the ground device comprises a wireless remote control transmitter, a data transmission terminal and a ground control computer system; the ground control computer system is connected with a RC (Remote Control) transmitter; the ground control computer system is also connected with the data transmission terminal; a sensor is integrated on the aircraft platform; the sensor measures the triaxial angular speed, the linear acceleration, the course angle, the triaxial positions and the triaxial linear speed of the aircraft platform.

Description

technical field [0001] The invention relates to a parameter identification test system for laying a flexible optical cable for a coaxial double-rotor unmanned helicopter, which belongs to the field of aviation technology. Background technique [0002] Because of its convenient take-off and landing, fixed-point hovering, and strong maneuverability, unmanned helicopters have a wide range of combat uses and have very considerable combat potential and development prospects. The countries that carried out the development of unmanned helicopters abroad include the United States, the United Kingdom, Canada, and Germany. Among them, the United States began to study unmanned helicopters in the 1950s. In the 1960s, the QH-50A anti-submarine remote control helicopter was successfully tested. During the Vietnam War, the US Army used the QH-50D unmanned helicopter to perform tasks such as reconnaissance, battlefield surveillance, and artillery target observation. Due to the many difficu...

Claims

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Application Information

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IPC IPC(8): G02B6/46
CPCG01C23/005G02B6/46
Inventor 不公告发明人
Owner SHENZHEN MINGXIN AVIATION TECH
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