CN109353491A - A kind of airborne computer cockpit handle instruction identification method - Google Patents
A kind of airborne computer cockpit handle instruction identification method Download PDFInfo
- Publication number
- CN109353491A CN109353491A CN201811053942.0A CN201811053942A CN109353491A CN 109353491 A CN109353491 A CN 109353491A CN 201811053942 A CN201811053942 A CN 201811053942A CN 109353491 A CN109353491 A CN 109353491A
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- Prior art keywords
- handle
- cockpit
- airborne computer
- cockpit handle
- state
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
Abstract
The present invention relates to a kind of airborne computer cockpit handle instruction identification methods, wherein according to the actual conditions of aircraft, airborne computer is gone forward rear cockpit handle status command by cognitron, is resolved respective handling by logic, is exported about undercarriage, the control signal of backplate folding and unfolding.The operation can adapt to the actual conditions of aircraft, using software mode solve the certain components of Aircraft landing gear system stop switch cannot normally in place the case where.It is operated by this, Landing Gear System can be controlled and carry out fault-tolerant processing, while the reliability that airborne computer controls undercarriage also can be enhanced, therefore reliability, safety and the maintainability of Aircraft landing gear system can be improved.
Description
Technical field
The present invention relates to a kind of handle instruction identification methods, refer to more particularly, to a kind of airborne computer cockpit handle
Enable recognition methods.
Background technique
Undercarriage belongs to the important component of aircraft, is mainly used for taking off, land and support aircraft is simultaneously when ground taxi
For ground moving, the single-attachment device that aircraft safety takes off, lands is ensured.Therefore, the workability of landing gear control system
Safety, mobility and the fight capability of aircraft can be directly influenced.
Currently, the undercarriage of modern aircraft is usually retractable, generally by the way of hydraulic-driven and electrical control
To realize the folding and unfolding of undercarriage.In Landing Gear System control, traditional control means are by fax Mechanical course, timeliness
Difference, lacks that faults-tolerant control, condition monitoring, maloperation differentiates and the measures such as shielding, signal detecting.In consideration of it, being airborne meter herein
Calculation machine is based on handle instruction identification and realizes Landing Gear System autonomous control and real-time status monitoring, is a kind of airborne computer cockpit
Handle instruction identification technology is gone forward according to the machine of coming from, the instruction of rear cockpit handle realizes machine according to the rules (the preferential front deck of rear deck)
Upper Landing Gear System undercarriage, backplate folding and unfolding control.
Summary of the invention
Goal of the invention:
The object of the present invention is to provide a kind of airborne computer cockpit handle instruction identification methods, wherein airborne computer
It is instructed by cockpit handle on receiver, by instruction identification, output, realizes undercarriage, backplate folding and unfolding control, improve aircraft and rise
Fall reliability, safety and the maintainability of frame system.
Technical solution:
The present invention provides a kind of airborne computer cockpit handle instruction identification method, wherein airborne computer identifies front stall
The state of cabin handle and rear cockpit handle then controls the folding and unfolding movement of undercarriage；And wherein, forward cockpit handle, which has, receives
Upper, down state, rear cockpit handle, which has, receives upper, neutral, down state.
In a preferred embodiment, airborne computer cockpit handle instruction identification method may include: 1) airborne calculating
When machine is opened, airborne computer initializes the state of front and back cockpit handle, and carries out instruction screen to front and back cockpit handle
Cover processing；2) it after airborne computer gets the status signal of Landing Gear System and front and back cockpit handle, is patrolled according to undercarriage
Electrical control requirement is collected, logic criterion first is carried out to the status signal of Landing Gear System, then believe the state of front and back cockpit handle
It number is handled.
In a preferred embodiment, if airborne computer cockpit handle instruction identification method may include: before indicating
In the receipts of cockpit handle, the status signal of down state simultaneously it is effective, then airborne computer setting forward cockpit handle state letter
It is number invalid；If indicate in the receipts of rear cockpit handle, the status signal of down state it is effective simultaneously, after airborne computer setting
The status signal of cockpit handle is invalid.
In a preferred embodiment, if airborne computer cockpit handle instruction identification method may include: rear cockpit
The status signal of handle changes, then airborne computer obtains the status signal of rear cockpit handle and sets rear cockpit handle
Change flag；If the status signal of forward cockpit handle changes, airborne computer obtains the state letter of forward cockpit handle
Number and set forward cockpit handle change flag.
In a preferred embodiment, airborne computer cockpit handle instruction identification method may include: when aircraft is in
When airborne status: 1) when rear cockpit handle is from neutral state change to when receiving upper state or down state, airborne computer is to preceding
Cockpit handle carries out instruction shielding processing, and obtains the status signal of rear cockpit handle；2) when rear cockpit handle goes up state from receipts
Or down state, when changing to neutral condition, airborne computer carries out instruction shielding processing to forward cockpit handle first, and then
It is handled as follows: if the status signal of rear cockpit handle is unchanged, obtaining the status signal of forward cockpit handle；And work as
When aircraft is in the state of ground: 3) when rear cockpit handle is from neutral state change to when receiving upper state, airborne computer is to back seat
Cabin handle carries out instruction shielding processing；4) when rear cockpit handle changes to neutral condition from the upper state of receipts or down state, then
The status signal of state in the receipts of airborne computer shielding instruction forward cockpit handle.
The utility model has the advantages that
Using airborne computer cockpit handle instruction identification method of the invention, for Aircraft landing gear system, realizing will
Landing Gear System carries out synthesization management, monitors and controls, and improves the efficiency of Aircraft landing gear system control, makes undercarriage system
System is intelligent, is conducive to merging for aircraft utilities system and avionics system data；It, can be in real time by computer autonomous control mode
Landing Gear System state is monitored, early warning is carried out to the potential failure of Landing Gear System in advance, pilot is prompted to make disposition early,
Improve the reliability of Landing Gear System control；Using computer from master mode, reduce the control unit under traditional control method,
There is positive effect to mitigating aircraft weight and reducing aircraft cost.Improve reliability, the safety of Aircraft landing gear system
And it is maintainable, it ensures flight safety, there is relatively broad application value.
Detailed description of the invention
Fig. 1 is on-off control system composition block diagram.
Specific embodiment
The invention will be described in further detail with reference to the accompanying drawing, please refers to Fig. 1.
For airborne computer cockpit handle instruction identification method of the invention, it is based on airborne computer hardware platform,
Using discrete magnitude acquisition module+control module+undercarriage control module mode, realize that Aircraft landing gear system is highly reliable, Gao An
Full control.
It is real-time by the discrete magnitude acquisition module of airborne computer according to aircraft blow the gear down process and gear up process
Landing Gear System relevant parameter is acquired, undercarriage is monitored in real time, the order of undercarriage handle is correctly identified；
Control logic operation is carried out to Landing Gear System relevant parameter by control module, by Landing Gear System control instruction, undercarriage
Position signal and correlated condition are output to undercarriage control module, while undercarriage on back production aircraft in the form of Digital Discrete amount
Actuation result is compared by actuation equipment implementing result with operation result at the appointed time, completes landing gear control system
Closed loop detection, and synchronism output to cockpit instruction system.
In airborne computer cockpit handle instruction identification method of the invention, according to the actual conditions of aircraft, airborne meter
Calculation machine is gone forward rear cockpit handle status command by cognitron, according to rear deck prior to front deck principle, by logical operation and is sentenced
It is disconnected, control instruction needed for outlet terminal Landing Gear System, realized by the control to each valve of hydraulic system undercarriage and
Backplate retractable movement, and the undercarriage of Landing Gear System and backplate retractable action situation and fault condition are sent to cockpit and referred to
Show system, prompts pilot to understand the working condition of Landing Gear System in real time, to carry out respective handling；It enhances simultaneously airborne
Computer is to Landing Gear System control task reliability；To which the reliability and safety of Aircraft landing gear system can be improved.
The on/off control instruction of Landing Gear System control mechanism is exported in the form of discrete magnitude, and control mechanism is
One efficient, reliable discrete magnitude closed-loop control system.
Airborne computer is controlled using electromagnetic relay switch amount, and electromagnetic relay is low with control voltage, drives
The features such as streaming current is small, direct current or pulse voltage can do control voltage.Airborne computer uses special Landing Gear System control
Molding block is inserted into 2 pieces of undercarriage control modules in computer altogether, has 15 way switch amount output interfaces as output interface is controlled
Ability.
Claims (5)
1. a kind of airborne computer cockpit handle instruction identification method, wherein airborne computer identifies forward cockpit handle and back seat
The state of cabin handle then controls the folding and unfolding movement of undercarriage；And wherein, forward cockpit handle, which has, receives upper, down state, after
Cockpit handle, which has, receives upper, neutral, down state.
2. airborne computer cockpit handle instruction identification method according to claim 1, it is characterised in that:
1) when airborne computer is opened, airborne computer initializes the state of front and back cockpit handle, and to front and back cockpit
Handle carries out instruction shielding processing；And
2) after airborne computer gets the status signal of Landing Gear System and front and back cockpit handle, according to undercarriage logic electricity
The requirement of gas control system first carries out logic criterion to the status signal of Landing Gear System, then to the status signal of front and back cockpit handle into
Row processing.
3. airborne computer cockpit handle instruction identification method according to claim 1, it is characterised in that: if before instruction
In the receipts of cockpit handle, the status signal of down state simultaneously it is effective, then airborne computer setting forward cockpit handle state letter
It is number invalid；If indicate in the receipts of rear cockpit handle, the status signal of down state it is effective simultaneously, after airborne computer setting
The status signal of cockpit handle is invalid.
4. airborne computer cockpit handle instruction identification method according to claim 1, it is characterised in that: if rear cockpit
The status signal of handle changes, then airborne computer obtains the status signal of rear cockpit handle and sets rear cockpit handle
Change flag；If the status signal of forward cockpit handle changes, airborne computer obtains the state letter of forward cockpit handle
Number and set forward cockpit handle change flag.
5. airborne computer cockpit handle instruction identification method according to claim 1, it is characterised in that:
When aircraft is in airborne status:
1) when rear cockpit handle is from neutral state change to when receiving upper state or down state, airborne computer is to forward cockpit handle
Instruction shielding processing is carried out, and obtains the status signal of rear cockpit handle；
2) when rear cockpit handle changes to neutral condition from the upper state of receipts or down state, airborne computer is first to forward cockpit
Handle carries out instruction shielding processing, and is then handled as follows: if the status signal of rear cockpit handle is unchanged, obtaining
The status signal of forward cockpit handle；And
When aircraft is in the state of ground:
3) when rear cockpit handle is from neutral state change to when receiving upper state, airborne computer carries out instruction screen to rear cockpit handle
Cover processing；
4) when rear cockpit handle changes to neutral condition from the upper state of receipts or down state, then before airborne computer shielding instruction
The status signal of state in the receipts of cockpit handle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811053942.0A CN109353491B (en) | 2018-09-11 | 2018-09-11 | Airborne computer cockpit handle instruction identification method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811053942.0A CN109353491B (en) | 2018-09-11 | 2018-09-11 | Airborne computer cockpit handle instruction identification method |
Publications (2)
| Publication Number | Publication Date |
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| CN109353491A true CN109353491A (en) | 2019-02-19 |
| CN109353491B CN109353491B (en) | 2022-08-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811053942.0A Active CN109353491B (en) | 2018-09-11 | 2018-09-11 | Airborne computer cockpit handle instruction identification method |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6927702B2 (en) * | 2001-06-11 | 2005-08-09 | Robert D. Wiplinger | Landing gear warning system |
| CN103640692A (en) * | 2013-11-28 | 2014-03-19 | 陕西千山航空电子有限责任公司 | Handle-based autonomous control method of training plane undercarriage system |
| CN103754358A (en) * | 2014-01-10 | 2014-04-30 | 深圳市大疆创新科技有限公司 | Method and device for controlling undercarriage of unmanned aerial vehicle |
| CN104369860A (en) * | 2014-11-27 | 2015-02-25 | 江西洪都航空工业集团有限责任公司 | Integrated type retracting-dropping priority control switch of landing gear |
| CN104709463A (en) * | 2015-02-05 | 2015-06-17 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Main landing gear control method and device |
| CN105000172A (en) * | 2015-07-27 | 2015-10-28 | 江西洪都航空工业集团有限责任公司 | Launch and recovery electrical control system of aircraft landing gear |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
-
2018
- 2018-09-11 CN CN201811053942.0A patent/CN109353491B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6927702B2 (en) * | 2001-06-11 | 2005-08-09 | Robert D. Wiplinger | Landing gear warning system |
| CN103640692A (en) * | 2013-11-28 | 2014-03-19 | 陕西千山航空电子有限责任公司 | Handle-based autonomous control method of training plane undercarriage system |
| CN103754358A (en) * | 2014-01-10 | 2014-04-30 | 深圳市大疆创新科技有限公司 | Method and device for controlling undercarriage of unmanned aerial vehicle |
| CN104369860A (en) * | 2014-11-27 | 2015-02-25 | 江西洪都航空工业集团有限责任公司 | Integrated type retracting-dropping priority control switch of landing gear |
| CN104709463A (en) * | 2015-02-05 | 2015-06-17 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Main landing gear control method and device |
| CN105000172A (en) * | 2015-07-27 | 2015-10-28 | 江西洪都航空工业集团有限责任公司 | Launch and recovery electrical control system of aircraft landing gear |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
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| CN109353491B (en) | 2022-08-23 |
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