Non-similar dual-redundancy integrated navigation device applied to unmanned plane

An integrated navigation and integrated navigation system technology, applied in the field of dissimilar dual-redundant integrated navigation devices, can solve the problems of inability to provide angular rate information around the axis of the aircraft body, complex power supply system, large volume and weight, etc., to improve reliability. And the effect of safety, high navigation accuracy, and high equipment reliability

Inactive Publication Date: 2014-12-03
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

However, because the platform inertial navigation system needs electromechanical control components to stabilize the platform in the inertial space, the volume and weight are large, the power supply system is complicated, and the cost is high. Usually, a single redundancy configuration is used, and the reliability is low.
In addition, the platform iner

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  • Non-similar dual-redundancy integrated navigation device applied to unmanned plane
  • Non-similar dual-redundancy integrated navigation device applied to unmanned plane

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Embodiment Construction

[0024] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0025] as attached figure 1 As shown, a non-similar dual-redundancy integrated navigation device applied to unmanned aerial vehicles, the integrated navigation device is installed in the corresponding position of the equipment cabin of the unmanned aerial vehicle, and is powered by the onboard power supply system; the integrated navigation device and the differential GPS ground Stations, flight control and management computers, and air data computer equipment have information cross-linking relationships.

[0026] The integrated navigation device includes: a laser strapdown inertial-satellite integrated navigation system, a fiber optic strapdown inertial-satellite integrated navigation system, a differential transmission station and an antenna.

[0027] The laser strapdown inertial-satellite integrated navigation system is the main integrate...

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Abstract

The invention discloses a non-similar dual-redundancy integrated navigation device applied to an unmanned plane, comprising main and standby combined navigation systems and a difference data transmission radio, wherein a laser strapdown inertia-satellite combined navigation system is adopted as the main combined navigation system which comprises a laser strapdown inertia navigation part and a satellite receiver; an optical fiber strapdown inertia-satellite combined navigation system is adopted as the standby combined navigation system which comprises an optical fiber strapdown inertia navigation part and a satellite receiver; the satellite receivers are both used for receiving GPS difference information, carrying out difference correction resolving and outputting satellite positioning information; the strapdown inertia navigation parts are both used for receiving atmosphere information and control commands and simultaneously outputting navigation information; the main and standby combination navigation systems transmit respectively received atmosphere information and satellite positioning information via serial interfaces. The device has the advantages of high reliability, good maintenance and lowering of requirements on a power supply caused by volume, weight and cost, providing of plane shaft angular rate information, high navigation precision and practicability.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicle navigation, and refers to a non-similar dual-redundancy combined navigation device applied to unmanned aerial vehicles. Background technique [0002] Navigation is the technology or method of guiding a navigation carrier from a starting point to a destination. Due to the particularity of unmanned drones, the onboard navigation system is the fundamental guarantee for the autonomous flight of drones to complete multiple missions. [0003] Inertial Navigation System (INS for short) uses inertial components to sense the motion acceleration of aircraft or other carriers, and after integral calculation, the navigation parameters are calculated to determine the position of the carrier. INS has strong autonomy, can continuously provide various navigation information including attitude, position, and speed, and has the characteristics of fast speed, good dynamic performance, and high short-term accu...

Claims

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Application Information

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IPC IPC(8): G01C21/00G01C21/16G01S19/47G01S19/42
CPCG01C21/005G01S19/47
Inventor 方晓星王金提向锦武王瑛
Owner BEIHANG UNIV
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