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Dual-redundancy airborne flight control computer

A flight control computer and dual-redundancy technology, applied in the field of avionics, can solve problems such as reducing system reliability and increasing system complexity, and achieve the effects of reducing failure rate, improving reliability and ensuring availability

Active Publication Date: 2017-07-07
北京天恒长鹰科技股份有限公司
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

For the flight control computer, increasing the redundancy unit increases the complexity of the system, and improperly increasing the redundancy will reduce the reliability of the system

Method used

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  • Dual-redundancy airborne flight control computer
  • Dual-redundancy airborne flight control computer

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Embodiment Construction

[0026] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0027] 1. Hardware structure:

[0028] Such as figure 1 As shown, the airborne flight control computer of the present invention is mainly made up of three boards: main logic control board (hereinafter also referred to as logic control board 1), standby logic control board (hereinafter also referred to as logic control board 2) and scheduling boards. The scheduling board has a main slot and a backup slot, the main logic control bo...

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Abstract

The invention discloses a dual-redundancy airborne flight control computer, which comprises a main logic control board, a standby logic control board and a dispatching board, wherein the dispatching board is provided with a main slot and a standby slot; the main logic control board is arranged in the main slot; the standby logic control board is arranged in the standby slot; the main logic control board and the standby logic control board adopt different software architectures and hardware packages, and two sets of independent power supply modules are used for power supply respectively; the power supply module of the main logic control board is controlled in a unified mode by the standby logic control board and the dispatching board; and the power supply module of the standby logic control board is controlled in a unified mode by the main logic control board and the dispatching board. Thus, bases on a heterogeneous redundancy technique, the redundancy is provided for the core complicated part in the flight control computer, the fault rate of the flight control computer is reduced, the independent power supply modules and the control logics are used for isolating fault, the usability of the system in a condition of single point fault can be ensured, and the reliability of an unmanned aerial vehicle is improved.

Description

technical field [0001] The invention belongs to the technical field of avionics, and in particular relates to a dual-redundancy airborne flight control computer, which is used to improve the reliability of the airborne flight control computer. Background technique [0002] With the continuous development of unmanned aerial vehicles, the complexity of its onboard avionics system continues to increase, which brings about an increase in the probability of failure. As the key component of the UAV, the stability of the flight control computer directly affects the reliability of the flight control system, which in turn affects the flight safety and mission execution capabilities of the UAV. Therefore, designing a highly reliable flight control computer is one of the key elements to improve the overall performance of the UAV. [0003] Generally speaking, in addition to selecting high-reliability components, the most effective way to improve the reliability of the flight control co...

Claims

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Application Information

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IPC IPC(8): G05B9/03
CPCG05B9/03
Inventor 赵磊
Owner 北京天恒长鹰科技股份有限公司
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