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An engine system early warning isolation and redundancy protection system and method

An engine system and protection system technology, applied in the directions of engine components, engine ignition, engine starting, etc., can solve the problem of system isolation after the engine is installed, early warning safety protection measures, lack of safeguard measures, and hidden safety hazards in aircraft testing, etc. It can achieve the effect of ensuring personal and property safety, strong anti-interference ability of external environment, and improving safety and reliability.

Active Publication Date: 2022-05-10
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, there are domestic and foreign literatures aimed at the lack of safety protection for the misoperation of the engine system during the ground test, which leads to large safety hazards and lack of safeguard measures for the safety of the aircraft test. Effective system isolation and early warning safety protection measures after engine installation

Method used

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  • An engine system early warning isolation and redundancy protection system and method
  • An engine system early warning isolation and redundancy protection system and method
  • An engine system early warning isolation and redundancy protection system and method

Examples

Experimental program
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Effect test

Embodiment 1

[0057] An engine system early warning isolation and redundancy protection system, including an electromechanical integrated control system, an early warning and isolation control system, a cockpit isolation control unit, and a backup interlock unit, and the electromechanical integrated control system is respectively connected with a rotating motor, a starter, and an engine , and output signals to the early warning and isolation control system; the early warning and isolation control system are respectively connected with the cockpit isolation control unit and the backup chain unit, and output signals to the oscilloscope; the early warning and isolation control system includes a relay card group, the The electromechanical integrated control system outputs the risk signal of the electrical accessories of the engine to the relay card group, and the output terminals of the relay card group are connected with each executive accessory.

[0058] Further, the early warning and isolatio...

Embodiment 2

[0062] A method for early warning isolation and redundancy protection of an engine system, comprising the following steps:

[0063] Step S100: Identify the risk signal of the engine electrical accessories, and analyze the working condition logic; the risk signal of the engine electrical accessories includes the motor working signal with a rotating starter, the oxygen supply signal of the starter, the ignition signal of the starter, the oil supply signal of the starter, Engine oxygen supply signal, engine ignition signal;

[0064] Step S200: transfer the risk signal of the engine electrical accessories to the relay card group, and then output it to each executive accessory by the relay card group; At the same time, if the work order is allowed, the relay card group is connected, otherwise the relay card group is placed in the disconnected position;

[0065] The logic condition F of the output signal of the early warning and isolation control system is:

[0066]

[0067] Am...

Embodiment 3

[0094] This embodiment is optimized on the basis of Embodiment 2. In the step S200, the relay card group is initially connected, and each relay in the isolation circuit is disconnected when and only when the cockpit isolating switch is turned on.

[0095] Further, in the step S200, when the switch is triggered by mistake or the aircraft abnormally strings in the electrical signal, it will cause But in the air, the wheel load and the rotational speed are used as the relay group connection signal at the same time. At this time, Γ=1, the F output can be guaranteed to be 1; 2 ≥60%, so γ 2 =0, Γ=0; during the ground test, the engine is running, although n 2 ≥60%, but wheel load on the ground γ 1 =0, Γ=0, so the condition of Γ=1 will not be falsely triggered during the test run, and the operation control of cockpit intervention realizes on-demand control.

[0096] Other parts of this embodiment are the same as those of Embodiment 2 above, so details are not repeated here.

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Abstract

The invention discloses an engine system early warning isolation and redundancy protection system and method, which centrally isolates the key signals of the starter and the engine, prevents the engine from being accidentally started and its key accessories in the warehouse, and greatly improves the safety of the test. Effective protection of personal and property safety; at the same time, the establishment of isolation control based on cockpit intervention and air redundancy protection logic ensures the safety of ground tests and flights; finally, based on the new centralized signal conversion module of the early warning and isolation control system, high Reliability is sent to the aircraft's comprehensive data acquisition processor for records, which reduces the overall risk of the test and greatly improves the safety and reliability of the aircraft test. The invention guarantees that the engine will not be started by mistake or the key accessories of the engine system will work before the engine test run, the safety of the test is greatly improved, the personal and property safety is effectively guaranteed, and the normal test run of the engine during air flight is not affected at the same time. practicality.

Description

technical field [0001] The invention belongs to the technical field of engine early warning protection, and in particular relates to an engine system early warning isolation and redundancy protection system and method. Background technique [0002] After the engine is assembled on the aircraft, it is necessary to check the throttle control system, engine control system and other flight cross-linking signals on the aircraft. The normal test run can only be performed after the inspection is passed. Before the test run, the throttle, aircraft control, and engine control systems are often tested and inspected in the hangar. The ground power supply needs to be connected, and the system function inspection is carried out under the normal power-on condition of the whole aircraft. However, during power-on tests and system adjustments, it is often necessary to manipulate the accelerator system and turn on the key switches of the power control system. When the engine control system re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G07C5/08B64F5/60F02C7/26F02C7/264F02C7/268F02C9/00H04L12/40
CPCG07C5/085G07C5/0808B64F5/60H04L12/40F02C7/26F02C7/264F02C7/268F02C9/00H04L2012/4028
Inventor 李红邓乐武雷湘徐龙王一麟苏逸婷
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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