Unmanned helicopter flight control system with fault diagnosis ability

An unmanned helicopter, fault diagnosis technology, applied in general control systems, control/regulation systems, testing/monitoring control systems, etc.

Pending Publication Date: 2017-02-15
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Especially in the professional unmanned helicopte

Method used

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  • Unmanned helicopter flight control system with fault diagnosis ability
  • Unmanned helicopter flight control system with fault diagnosis ability
  • Unmanned helicopter flight control system with fault diagnosis ability

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Embodiment Construction

[0056] The present invention is an unmanned helicopter flight control system with fault diagnosis capability, which is composed of a navigation / flight control computer system, a sensor system, an actuator system, a remote control telemetry system and a power supply system; the relationship between them is as follows: / The flight control computer system is connected with the sensor system, the actuator system and the remote control and telemetry system through specific interface components to complete communication and data transmission; the sensor information of the sensor system is connected to the navigation / flight control computer system for navigation / flight control Calculation; the remote control and telemetry system adds a remote control, which is directly connected to the steering gear system through the remote control autonomous conversion, that is, the manual remote control line; the actuator system realizes the control according to the control signal output by the navi...

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Abstract

The invention discloses an unmanned helicopter flight control system with a fault diagnosis ability. The hardware device is composed of a navigation/flight control computer system, a sensor system, an execution mechanism system, a remote control and remote measurement system and a power supply system, wherein the navigation/flight control computer system is an active/standby dual-redundancy system; the sensor system provides sensor information for the navigation/flight control computer system; the remote control and remote measurement system is directly connected with an actuator system through remote control autonomous conversion; and the power supply system provides power for the sensor system, the navigation/flight control computer system and the remote control and remote measurement system. The software structure comprises a bottom operation system, a data I/O module, system management software, redundancy management software, flight control software, navigation control software and task execution software. Through adding the hardware redundancy to the flight control system of the invention, thereby enhancing the reliability; the retention of the remote control system can handle emergency states and non routine tasks; and due to the adding of the fault diagnosis method, the fault identifiability is enhanced.

Description

[0001] 1. Technical field [0002] The invention provides an unmanned helicopter flight control system with fault diagnosis capability, which relates to the scheme design of an unmanned helicopter flight control system with special functions, and belongs to the design field of unmanned helicopter flight control systems. [0003] 2. Background technology [0004] The flight control system is one of the very important core systems in the entire unmanned helicopter system, and it is also one of the difficulties in the development of the current unmanned helicopter system. At present, there are many flight control systems for unmanned helicopters on the market, but most of them are consumer-grade, which are far from the flight control systems used in engineering and military drone helicopters in terms of function and reliability. Consumer-grade drones only fly for ten minutes to dozens of minutes, generally no more than an hour. The above task load is mainly a simple camera, used ...

Claims

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Application Information

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IPC IPC(8): G05D1/10G05B23/02
CPCG05B23/0275G05D1/101
Inventor 王吉东王立新
Owner BEIHANG UNIV
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