CN109353491B

CN109353491B - Airborne computer cockpit handle instruction identification method

Info

Publication number: CN109353491B
Application number: CN201811053942.0A
Authority: CN
Inventors: 董鹏辉; 陈军
Original assignee: Shaanxi Qianshan Avionics Co Ltd
Current assignee: Shaanxi Qianshan Avionics Co Ltd
Priority date: 2018-09-11
Filing date: 2018-09-11
Publication date: 2022-08-23
Anticipated expiration: 2038-09-11
Also published as: CN109353491A

Abstract

The invention relates to a cockpit handle instruction identification method of an onboard computer, wherein according to the actual situation of an airplane, the onboard computer outputs control signals related to the retraction and release of an undercarriage and a protection plate by identifying handle state instructions of a front cockpit and a rear cockpit on the airplane and carrying out corresponding logic calculation processing. The operation can adapt to the actual situation of the airplane, and the situation that terminal electric doors of certain parts of the undercarriage system of the airplane cannot be normally in place is solved by adopting a software mode. Through the operation, the control of the undercarriage system can be subjected to fault-tolerant processing, and meanwhile, the reliability of the undercarriage control by the airborne computer can be enhanced, so that the reliability, the safety and the maintainability of the aircraft undercarriage system can be improved.

Description

Airborne computer cabin handle instruction identification method

Technical Field

The invention relates to a method for identifying a handle instruction, in particular to a method for identifying a handle instruction of an airborne computer cockpit.

Background

The landing gear belongs to an important component of an airplane, and is mainly used for supporting the airplane during take-off, landing and ground sliding and moving on the ground, so that the airplane can be safely taken off and landed. Thus, the operational performance of the landing gear control system directly affects the safety, maneuverability, and operational capabilities of the aircraft.

At present, the landing gear of modern aircraft is usually retractable, and the retraction of the landing gear is generally realized by adopting a hydraulic drive and an electric control mode. In the control of the landing gear system, the traditional control means is the control through an electric transmission machine, so that the timeliness is poor, and measures such as fault-tolerant control, state monitoring, misoperation judgment, shielding, hydraulic detection and the like are lacked. In view of the above, the technology realizes the autonomous control and the real-time state monitoring of the undercarriage system based on the handle instruction identification by the airborne computer, is an airborne computer cockpit handle instruction identification technology, and realizes the retraction control of the undercarriage and the guard plate of the undercarriage system on the airplane according to the instructions from the handles of the front and rear cabs on the airplane and the regulations (the front cab is preferred by the rear cab).

Disclosure of Invention

The purpose of the invention is as follows:

the invention aims to provide a cockpit handle instruction identification method for an onboard computer, wherein the onboard computer realizes the retraction and release control of an undercarriage and a protection plate through the upper cockpit handle instruction of a receiver and through instruction identification and output, and the reliability, the safety and the maintainability of an aircraft undercarriage system are improved.

The technical scheme is as follows:

the invention provides a method for identifying instructions of a handle of a cockpit by an airborne computer, wherein the airborne computer identifies the states of a handle of a front cockpit and a handle of a rear cockpit, and then controls the retraction and release actions of an undercarriage; and wherein, the front cockpit handle has the state of receiving, putting down, and back cockpit handle has the state of receiving, neutral, putting down.

In a preferred embodiment, the on-board computer cockpit handle command identification method may include: 1) when the on-board computer is started, the on-board computer initializes the state of the handles of the front and rear cabins and conducts instruction shielding processing on the handles of the front and rear cabins; 2) after the onboard computer acquires the state signals of the undercarriage system and the handles of the front and rear cabins, logic criterion is firstly carried out on the state signals of the undercarriage system according to the logic electrical control requirement of the undercarriage, and then the state signals of the handles of the front and rear cabins are processed.

In a preferred embodiment, the on-board computer cockpit handle command identification method may include: if the state signals indicating the receiving-up and putting-down states of the front cabin handle are simultaneously valid, the state signals of the front cabin handle set by the airborne computer are invalid; if the state signals indicating the up and down states of the handle of the rear cabin are simultaneously valid, the state signals of the handle of the rear cabin set by the onboard computer are invalid.

In a preferred embodiment, the on-board computer cockpit handle command identification method may include: if the state signal of the handle of the rear cockpit changes, the onboard computer acquires the state signal of the handle of the rear cockpit and sets a change mark of the handle of the rear cockpit; if the state signal of the front cabin handle changes, the on-board computer acquires the state signal of the front cabin handle and sets a front cabin handle change flag.

In a preferred embodiment, the on-board computer cockpit handle command identification method may include: when the aircraft is in the air state: 1) when the rear cockpit handle changes from the neutral state to the on-state or the off-state, the onboard computer shields the front cockpit handle and acquires a state signal of the rear cockpit handle; 2) when the rear cabin handle changes from the up state or the down state to the neutral state, the on-board computer firstly conducts command shielding processing on the front cabin handle and then conducts the following processing: if the state signal of the handle of the rear cockpit has no change, acquiring the state signal of the handle of the front cockpit; and when the aircraft is in a ground state: 3) when the handle of the rear cockpit changes from the neutral state to the on-board state, the on-board computer carries out instruction shielding processing on the handle of the rear cockpit; 4) when the rear cabin handle changes from the stowed or lowered state to the neutral state, the onboard computer then masks the status signal indicating the stowed state of the front cabin handle.

Has the advantages that:

by adopting the onboard computer cockpit handle instruction identification method, the undercarriage system is comprehensively managed, monitored and controlled aiming at the undercarriage system, the control efficiency of the undercarriage system is improved, the undercarriage system is intelligentized, and the data fusion of an electromechanical system and an avionic system of an airplane is facilitated; by means of the autonomous control mode of the computer, the state of the undercarriage system can be monitored in real time, potential faults of the undercarriage system are early warned, a pilot is prompted to deal with the faults as soon as possible, and the reliability of control of the undercarriage system is improved; and a computer autonomous mode is adopted, so that control components in the traditional control mode are reduced, and the method has positive significance for reducing the weight of the airplane and the cost of the airplane. The reliability, the safety and the maintainability of the aircraft landing gear system are improved, the flight safety is guaranteed, and the aircraft landing gear system has a wide application value.

Drawings

Fig. 1 is a block diagram of a switch control system.

Detailed Description

The invention is described in further detail below with reference to the accompanying drawings, which refer to fig. 1.

The method for identifying the command of the cockpit handle of the airborne computer is based on an airborne computer hardware platform, and realizes high-reliability and high-safety control of an aircraft landing gear system by adopting a mode of a discrete quantity acquisition module, a control module and a landing gear control module.

According to the undercarriage releasing process and the undercarriage retracting process of the airplane, relevant parameters of an undercarriage system are collected in real time through a discrete quantity collecting module of an onboard computer, the undercarriage state is monitored in real time, and an undercarriage handle command is correctly identified; the control module is used for carrying out control logic operation on relevant parameters of the undercarriage system, outputting control instructions of the undercarriage system, undercarriage position signals and relevant states to the undercarriage control module in a digital discrete quantity mode, simultaneously extracting execution results of actuation equipment of the undercarriage on the airplane, comparing the actuation results with the operation results within specified time, completing closed-loop detection of the undercarriage control system, and synchronously outputting the closed-loop detection to a cabin indication system.

According to the actual situation of the airplane, the onboard computer outputs a control instruction required by a terminal undercarriage system through logical operation and judgment by identifying the handle state instructions of front and rear cabins on the airplane according to the principle that the rear cabin is prior to the front cabin, realizes the receiving and releasing actions of the undercarriage and the guard plate through controlling each valve of a hydraulic system, sends the receiving and releasing action conditions and the fault conditions of the undercarriage and the guard plate of the undercarriage system to a cockpit indication system, and prompts a pilot to know the working state of the undercarriage system in real time so as to carry out corresponding processing; meanwhile, the reliability of the control task of the undercarriage system by the airborne computer is enhanced; thus, the reliability and safety of the aircraft landing gear system may be improved.

The starting/closing control instruction of the landing gear system control mechanism is output in a discrete quantity mode, and the control mechanism is an efficient and reliable discrete quantity closed-loop control system.

The on-board computer controls the switching value by adopting an electromagnetic relay, and the electromagnetic relay has the characteristics of low control voltage, small driving current, capability of controlling voltage by using direct current or pulse voltage and the like. The airborne computer adopts a special undercarriage system control module as a control output interface, 2 undercarriage control modules are inserted into the computer, and the computer has the capacity of 15-path switching value output interfaces.

Claims

1. An onboard computer cabin handle instruction identification method is disclosed, wherein an onboard computer identifies the states of a front cabin handle and a rear cabin handle and then controls the retraction and release actions of an undercarriage; and wherein, the front cockpit hand grip has the state of receiving and putting down, the back cockpit hand grip has the state of receiving, neutral, putting down;

wherein the method comprises the following steps:

1) when the on-board computer is started, the on-board computer initializes the state of the handles of the front and rear cabins and conducts instruction shielding processing on the handles of the front and rear cabins; and is

2) After an onboard computer acquires state signals of an undercarriage system and front and rear cabin handles, logic criterion is firstly carried out on the state signals of the undercarriage system according to logic electrical control requirements of the undercarriage, and then the state signals of the front and rear cabin handles are processed:

when the aircraft is in the air state:

when the rear cockpit handle changes from the neutral state to the on-state or the off-state, the onboard computer shields the front cockpit handle and acquires a state signal of the rear cockpit handle;

when the rear cabin handle changes from the up state or the down state to the neutral state, the on-board computer firstly conducts command shielding processing on the front cabin handle and then conducts the following processing: if the state signal of the handle of the rear cockpit has no change, acquiring the state signal of the handle of the front cockpit; and is

When the aircraft is in a ground state:

when the handle of the rear cockpit changes from the neutral state to the on-board state, the on-board computer carries out instruction shielding processing on the handle of the rear cockpit;

when the rear cabin handle changes from the up state or the down state to the neutral state, the on-board computer shields a state signal indicating the up state of the front cabin handle.

2. The on-board computer cockpit handle command identification method of claim 1, wherein: in the step 2), the logic criterion of the state signal of the landing gear system is as follows: if the state signals indicating the up and down states of the front cabin handle are simultaneously valid, the state signals of the front cabin handle set by the airborne computer are invalid; if the state signals indicating the up and down states of the handle of the rear cabin are simultaneously valid, the state signals of the handle of the rear cabin set by the onboard computer are invalid.

3. The on-board computer cabin handle instruction recognition method of claim 1, wherein: in the step 2), the state signals of the front and rear cabin handles are processed as follows: if the state signal of the handle of the rear cockpit changes, the onboard computer acquires the state signal of the handle of the rear cockpit and sets a change mark of the handle of the rear cockpit; if the state signal of the front cabin handle changes, the on-board computer acquires the state signal of the front cabin handle and sets a front cabin handle change flag.