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Main and standby control switching system and method for civil aircraft actuators

A technology for switching systems and actuators, applied in general control systems, control/regulation systems, computer control, etc., to achieve high availability and meet safety design requirements

Pending Publication Date: 2020-11-13
XIAN FLIGHT SELF CONTROL INST OF AVIC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is no public information about the switching logic of the active and standby working modes of civil aircraft actuators

Method used

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  • Main and standby control switching system and method for civil aircraft actuators
  • Main and standby control switching system and method for civil aircraft actuators
  • Main and standby control switching system and method for civil aircraft actuators

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Embodiment Construction

[0057] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.

[0058] The steps shown in the flowcharts of the figures may be performed in a computer system, such as a set of computer-executable instructions. Also, although a logical order is shown in the flowcharts, in some cases the steps shown or described may be performed in an order different from that shown or described herein.

[0059] The embodiment of the present invention proposes an active-standby control switching system and method for civil aircraft actuators. Aiming at the remote control electronic architecture of redundant actuators of civil aircraft that adopt the active-...

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Abstract

The embodiment of the invention discloses a main and standby control switching system and method for civil aircraft actuators. The system comprises a main REU, a standby REU, a main actuator, a standby actuator, a first ACE, a second ACE and an FCM. The FCM sends a control instruction to the two ACEs; the ACE sends the received control instruction to the REU connected with the ACE; the main REU isconnected with the main actuator according to the control instruction and controls the movement of the control surface through the main actuator; the standby REU cuts off the standby actuator according to the control instruction; the main REU cuts off the main actuator according to a main-standby switching condition preset in the main REU, and sends an off state of the main actuator to the standby REU; and the standby REU switches on the standby actuator according to the switching-off state of the main actuator and sends the switching-on state of the standby actuator to the main REU. The embodiment of the invention aims at a civil aircraft redundancy actuator remote control electronic architecture adopting a main / standby working mode, and realizes a remote control electronic main / standbyselection mode meeting the requirements of high safety and high availability.

Description

technical field [0001] The invention relates to but not limited to the technical field of safety design of civil aircraft flight control systems, in particular to a system and method for switching main and backup control of civil aircraft actuators. Background technique [0002] The main control surfaces (elevator, aileron, and rudder) of civil aircraft are usually designed with redundancy to meet the system safety requirements. In this design, multiple actuators are installed on each rudder surface, and each actuator can independently control the deflection of the rudder surface. When one actuator fails, other actuators can still maintain control of the rudder surface. meet performance requirements. [0003] The above-mentioned multi-actuator architecture generally has two control modes: main-main working mode and main-standby working mode. In the main-main working mode, the actuators are in working state at the same time; in the main-standby working mode, under normal ci...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/042
CPCG05B19/0423G05B2219/25257
Inventor 刘宏明贾凡张航
Owner XIAN FLIGHT SELF CONTROL INST OF AVIC