CN103879545B - Cabin door flight lock system for an aircraft - Google Patents
Cabin door flight lock system for an aircraft Download PDFInfo
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- CN103879545B CN103879545B CN201410106296.5A CN201410106296A CN103879545B CN 103879545 B CN103879545 B CN 103879545B CN 201410106296 A CN201410106296 A CN 201410106296A CN 103879545 B CN103879545 B CN 103879545B
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- 230000005611 electricity Effects 0.000 claims description 9
- 230000007246 mechanism Effects 0.000 claims description 9
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- 230000008901 benefit Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 description 2
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Abstract
The invention relates to a cabin door flight lock system for an aircraft, comprising a logic processing and control unit configured to generate a first cabin door lock signal from an on-wheel bus signal, an airspeed bus signal, a cabin door closing sensor signal; the door flight lock system also includes flight lock logic configured to generate a second door lock signal to indicate that a door of the aircraft is set to the locked state or the unlocked state based on the first door lock signal and the on-board hard-wire signal. According to the cabin door flight lock system, the cabin door can be prevented from being opened due to misoperation in the flight process of the aircraft, the normal opening and emergency evacuation requirements of the cabin door can not be hindered, and meanwhile, single-point failure can be avoided through the design of the control framework of the cabin door flight lock system, so that the airworthiness clause requirements can be fully met, and the safety of the aircraft can be ensured.
Description
Technical field
The present invention relates to aircraft security field, the lock in particular it relates to a kind of hatch door for aircraft flies
System.
Background technology
The nineties experienced twice after cargo door accident, FAA issued FAR25-114 amendments in 2004, to cabin
Door safety standard proposes very strict requirement.According to the requirement of newest clause, during the door design of aircraft, it is necessary to
Having measure prevents each hatch door from awing being opened unintentionally by people, meanwhile, if these precautionary measures include being filled using auxiliary
Put, then these devices and its control system must be designed to：
(1) single point failure will not hinder multiple outlets to be opened；With
(2) it is impossible that the failure that outlet is opened is hindered after landing.
Herein, single point failure is referred in the logical process and control unit of hatch door, due to single sensing device or
The failure (signal of such as power down or output error etc.) of control device and lead to not open hatch door situation.
In order to the flight safety for ensureing aircraft exists ensureing aircraft, it is necessary to design a kind of safe flight lock control system
Will not be opened unintentionally in flight course, meanwhile, the normal opening of hatch door will not be hindered again, meet performance requirement and safety will
Ask.
The content of the invention
It is an object of the invention to provide a kind of safe and reliable hatch door flight lock system for aircraft, it can either
Prevent hatch door from being opened because of maloperation in the flight course of aircraft, will not also hinder the normal opening and emergency evacuation of hatch door
Demand, meanwhile, by its control framework be designed to avoid single point failure, so as to fully meet the requirement of seaworthiness clause simultaneously
And ensure that the safety of aircraft.
To achieve the above object, the invention provides a kind of hatch door flight lock system for aircraft, it is characterised in that
Including logical process and control unit, the logical process and control unit are configured to total according to wheel load bus signals, air speed
Line signal, hatch door closure sensor signal generation the first hatch door lock signal；The hatch door flight lock system is also patrolled including flight lock
Unit is collected, the flight lock logic unit is configured to according to the first hatch door lock signal and wheel load hard signal generation second
Hatch door lock signal, to control for the hatch door of the aircraft to be set to locking state or released state.Exist in this way
Generate for controlling to have considered wheel load hard signal during the second hatch door lock signal of the hatch door of aircraft such that it is able to effectively
Avoid single point failure, and then improve the demand for security of aircraft.
According to a kind of implementation method of hatch door flight lock system of the invention, when following condition is met simultaneously：Institute
State wheel load bus signals and indicate the aircraft not on the ground；The air speed bus signals indicator air speed is more than predetermined air speed
Threshold value；And hatch door described in the hatch door closure sensor signal designation is closed, then the logical process and control
The first hatch door lock signal that unit is generated is lock signal on first.Generating the first hatch door lock signal in this way
When considered wheel load bus signals, air speed bus signals and hatch door closure sensor, and set its need it is simultaneously full
The certain condition of foot, so as to improve the reliability of the first generated hatch door lock signal.
According to a kind of implementation method of hatch door flight lock system of the invention, when the first hatch door lock signal is the
On one lock signal and the wheel load hard signal indicate the aircraft not on the ground when, the second cabin door lock letter for being generated
Number just indicate for the hatch door of the aircraft to be set to locking state.
Hatch door is set by analyzing multiple input signals according to the hatch door flight lock system for aircraft of the invention
Lock or unlock, so as to avoid that the hatch door is inadvertently opened during high-speed flight in the air, and ensure at ground or
The hatch door can be normally opened when air speed is less than airspeed threshold, this improves the security of the hatch door flight lock system
And reliability.Additionally, the wheel load hard signal in the input of the flight lock logic unit can be avoided by institute
State the problem that hatch door caused by the single point failure in logical process and control unit cannot be opened under normal circumstances.
Brief description of the drawings
Fig. 1 shows the functional schematic according to hatch door flight lock system of the invention；And
Fig. 2 shows the control logic figure according to hatch door flight lock system of the invention.
Specific embodiment
Figure 1 illustrates the functional schematic according to hatch door flight lock system of the invention.It can be seen that should
Hatch door flight lock system includes logical process and control unit 9, flight lock logic unit 4 and actuating mechanism 16.Wherein, logic
Treatment and control unit 9 include that wheel load bus signals judgment means 5, air speed bus signals judgment means 6, hatch door are closed and judge dress
7 and upper electric logic judgment device 8 are put, the logical process and control unit 9 receive wheel load bus signals 1, air speed bus signals
2nd, hatch door closure sensor signal 3 and the first hatch door lock signal of output.And wherein, flight lock logic unit 4 includes logic
Judgment means 13, flight lock logic unit 4 receives the first hatch door lock signal and wheel load hard signal 10 and exports the second cabin
Door lock signal；And wherein, actuating mechanism 16 includes internal relay 15, o 11 and hatch door mechanism for locking up 12,
The actuating mechanism is configured to that the hatch door of aircraft is set into locking state or released state according to the second hatch door lock signal.
According to hatch door flight lock system of the invention it is a kind of preferred embodiment in, wheel load bus signals judge dress
Whether 5 are put for according to judging aircraft on the ground in the wheel load bus signals 1 of logical process and the input of control unit 9
, when judging the aircraft not on the ground, the wheel load bus signals judgment means 5 output high level otherwise exports low electricity
It is flat.The wheel load bus signals can be that the output signal of multiple sensors on aircraft is transmitted after synthesis by bus by analysis
Signal.Air speed bus signals judgment means 6 are used to be believed according to the air speed bus in logical process and the input of control unit 9
Whether numbers 2 judge air speed more than predetermined airspeed threshold, when air speed is more than predetermined airspeed threshold, the air speed bus signals
Judgment means 6 export high level, otherwise export low level.Hatch door closes judgment means 7 to be used to analyze in logical process and control
The hatch door closure sensor signal 3 of the input of unit 9, when judging that the hatch door is closed, the hatch door is closed and judged
Device 7 exports high level, otherwise exports low level.The hatch door closure sensor signal 3 is exported by hatch door closure sensor, works as inspection
Measure hatch door it is in an open position when, hatch door closure sensor signal 3 be low level；It is in the closed position when hatch door is detected
When, then it is high level.Upper electric logic judgment device 8 is used to receive the judgement of wheel load bus signals judgment means 5, air speed bus signals
Device 6 and hatch door close the output signal of judgment means 7, and only when all of output signal is all high level, electricity is patrolled on this
Collect judgment means 8 and just export high level, otherwise export low level.The output signal of upper electric logic judgment device 8 is at logic
The output signal of reason and control unit 9, and the output signal is used as the input signal of flight lock logic unit 4.
According to above-mentioned implementation method, when the aircraft on the ground, such as multiple sensor energy at undercarriage
Enough (such as the sensor of tire on installation undercarriage) in several ways judges aircraft on the ground, and the plurality of sensing
The output signal of device is converted to wheel load bus signals and is sent to wheel load bus signals by the bus in aircraft after treatment
Judgment means 5.Wheel load bus signals judgment means 5 judge aircraft on ground by wheel load bus signals in this case
On, and the upper electric output of logic judgment device 8 low level.According to follow-up explanation, now hatch door will unblock.So design is excellent
Gesture is the demand that disclosure satisfy that the emergency escape when aircraft is on ground.
According to above-mentioned implementation method, such as surveyed positioned at aircraft or positioned at the air speed detection means of ground command center
The air speed of aircraft is obtained, and the airspeed signal is converted to air speed bus signals and is sent out by the bus in aircraft after treatment
Air speed bus signals judgment means 6 are given, when air speed bus signals judgment means 6 judge that aircraft is static or to be less than or equal to
When the speed of airspeed threshold is moved, the upper electric output of logic judgment device 8 low level.According to follow-up explanation, now hatch door will solution
Lock.The advantage of so design is that disclosure satisfy that occupant jumps the demand that cabin is withdrawn when aircraft is moved with relatively low speed.
According to above-mentioned implementation method, when hatch door is in open mode, the upper electric output of logic judgment device 8 low level.
According to follow-up explanation, now hatch door will unblock.The advantage of so design is that can avoid flying hatch door when hatch door is opened
Row is locked.
According to above-mentioned implementation method, hatch door is set to lock by the state for judging multiple signals, and the state of individual signals
Change just can result in hatch door unblock.The advantage of so design is condition that hatch door can be made to lock than the condition that hatch door is unlocked
It is tightened up, so that when there is single point failure (such as the wherein failure of certain judgment means 5,6 or 7), dress is judged by other
The normal work put and hatch door is normally opened be possible.
According to hatch door flight lock system of the invention it is a kind of preferred embodiment in, above-mentioned airspeed threshold is 80
Section, it will be understood by those of skill in the art that the airspeed threshold is designed to by other threshold values according to specific demand for security, for example
The other values such as 100 sections are also feasible.
According to hatch door flight lock system of the invention it is a kind of preferred embodiment in, when wheel load hard signal 10 is
During high level, it indicates that aircraft is not on the ground.In this case, logic judgment device 13 be used for analyze logical process and
The output signal and wheel load hard signal 10 of control unit 9, only when wheel load hard signal 10 and logical process and control list
When the output signal of unit 9 is all high level, logic judgment device 13 just exports high level, otherwise exports low level.Wherein, the wheel
It can be the output signal of multiple sensors on aircraft by analysis after synthesis by single wire transmission to carry hard signal 10
Signal.
According to above-mentioned implementation method, when there is the problem of single point failure in logical process and control unit 9, for example
When aircraft rest on the ground, logical process is caused because wheel load bus signals judgment means 5 mistakenly export high level
And during the output high level of control unit 9, or cause it can only to export electricity high due to the mistake in upper electric logic judgment device 8
Usually, logic judgment device 13 can be made to export low level by wheel load hard signal 10, according to follow-up explanation, now hatch door
Will unblock.The advantage of so design is that can avoid because the single point failure occurred in logical process and control unit 9 is asked
The situation inscribed and cause hatch door to open under normal circumstances.
According to hatch door flight lock system of the invention it is a kind of preferred embodiment in, only when logic judgment device
During 13 output high level, internal relay 15 is just switched on, and otherwise, internal relay 15 is not switched on.Only when internal relay
When device 15 is switched on, the ability of o 11 is for example, by electricity on 28V power supplys 14, otherwise, the power down of magnetic solenoid 11.And on hatch door
Latch mechanism is configured to make hatch door lock during the electricity on o 11, and hatch door is unlocked in 11 power down of o.
According to hatch door flight lock system of the invention it is a kind of preferred embodiment in, hatch door include landing gate, clothes
Business door or escape door.
Figure 2 illustrates the control logic figure according to hatch door flight lock system of the invention.In the step s 21, judge
Whether wheel load bus signals indicate aircraft not on the ground, in step S22, judge whether air speed bus signals indicate flight
The air speed of device is more than 80 sections.In step S23, judge whether hatch door closure sensor signal indicates hatch door to be closed,
If judging in S21, S22, S23 is all "Yes", "Yes" is judged in step s 24；If step S21, S22, S23
In it is any be judged to "No", then be judged to "No" in step s 24.Judge whether wheel load hard signal refers in step s 25
Show aircraft not on the ground.In step S26, if judging in S24 and S25 is all "Yes", into step S27
In, electric and hatch door is locked on solenoid；If being arbitrarily judged to "No" in S24 and S25, into step S28, helical
Pipe power down and hatch door unblock.
Hatch door is set by analyzing multiple input signals according to the hatch door flight lock system for aircraft of the invention
Lock or unlock, so as to avoid that the hatch door is inadvertently opened during high-speed flight in the air, and ensure at ground or
The hatch door can be normally opened when air speed is less than airspeed threshold, this improves the security of the hatch door flight lock system
And reliability.Additionally, the wheel load hard signal in the input of the flight lock logic unit can be avoided by institute
State the problem that hatch door caused by the single point failure in logical process and control unit cannot be opened under normal circumstances.
Although the foregoing describing specific embodiment of the invention, those skilled in the art can be in appended power
Profit makes various changes and modifications in the range of requiring.
Claims (15)
1. a kind of hatch door flight lock system for aircraft, it is characterised in that including：
Logical process and control unit (9), it is configured to according to wheel load bus signals (1), air speed bus signals (2), hatch door
Closure sensor signal (3) generates the first hatch door lock signal；
Flight lock logic unit (4), it is configured to be generated according to the first hatch door lock signal and wheel load hard signal (10)
Second hatch door lock signal, to control for the hatch door of the aircraft to be set to locking state or released state,
Wherein, when the wheel load hard signal (10) indicates the aircraft on the ground, the second cabin door lock letter for being generated
The hatch door of the aircraft is set to released state by number instruction.
2. hatch door flight lock system according to claim 1, it is characterised in that when following condition is met simultaneously：
The wheel load bus signals (1) indicate the aircraft not on the ground；
Air speed bus signals (2) indicator air speed is more than predetermined airspeed threshold；And
The hatch door closure sensor signal (3) indicates the hatch door to be closed,
The first hatch door lock signal that the logical process and control unit (9) are generated is lock signal on first.
3. hatch door flight lock system according to claim 1, it is characterised in that when following condition is met：
The wheel load bus signals (1) indicate the aircraft on the ground or
Air speed bus signals (2) indicator air speed less than predetermined airspeed threshold or
The hatch door closure sensor signal (3) indicates the hatch door to be in open mode,
The first hatch door lock signal that the logical process and control unit (9) are generated is the first unlocking signal.
4. hatch door flight lock system according to claim 2, it is characterised in that when the wheel load hard signal (10) indicates
The aircraft not on the ground when, the second hatch door lock signal for being generated just controls to be set to the hatch door of the aircraft
Lock status.
5. hatch door flight lock system according to claim 1, it is characterised in that the hatch door flight lock system also includes causing
Motivation structure (16), the actuating mechanism is configured to be set to the hatch door of the aircraft according to the second hatch door lock signal
Locking state or released state.
6. hatch door flight lock system according to claim 5, it is characterised in that the actuating mechanism (16) including inside after
Electrical equipment (15), o (11) and hatch door mechanism for locking up (12), the hatch door mechanism for locking up are configured in the electricity
The hatch door is locked during electricity on magnetic solenoid (11), unlock the hatch door in the o (11) power down.
7. hatch door flight lock system according to claim 1, it is characterised in that the logical process and control unit (9)
With for judge the aircraft whether wheel load bus signals judgment means (5) on the ground, when the wheel load bus letter
When number judgment means (5) judge the aircraft not on the ground by analyzing the wheel load bus signals (1), then electricity high is exported
It is flat, otherwise export low level.
8. hatch door flight lock system according to claim 1, it is characterised in that the logical process and control unit (9)
With for judging whether the air speed is more than air speed bus signals judgment means (6) of predetermined airspeed threshold, when the sky
Fast bus signals judgment means (6) judge that the air speed is more than the predetermined sky by analyzing the air speed bus signals (2)
During fast threshold value, then high level is exported, otherwise export low level.
9. hatch door flight lock system according to claim 1, it is characterised in that the logical process and control unit (9)
With judgment means (7) are closed for analyzing the hatch door of the hatch door closure sensor signal (3), only when the hatch door is closed
When judgment means (7) judge that the hatch door is closed by analyzing the hatch door closure sensor signal (3), just export
High level, otherwise exports low level.
10. hatch door flight lock system according to any one of claim 1 to 6, it is characterised in that the logical process and
Control unit (9) with for judge the aircraft whether wheel load bus signals judgment means (5) on the ground, for sentencing
Whether disconnected air speed closes biography more than air speed bus signals judgment means (6) of predetermined airspeed threshold, for analyzing the hatch door
The hatch door of sensor signal (3) closes judgment means (7) and upper electric logic judgment device (8)；When the wheel load bus signals are sentenced
When disconnected device (5) judges the aircraft not on the ground by analyzing the wheel load bus signals (1), then high level is exported,
Otherwise export low level；When the air speed bus signals judgment means (6) judge institute by analyzing the air speed bus signals (2)
When stating air speed more than the predetermined airspeed threshold, then high level is exported, otherwise export low level；Closed when the hatch door and judged
When device (7) judges that the hatch door is closed by analyzing the hatch door closure sensor signal (3), electricity high is just exported
It is flat, otherwise export low level；The upper electric logic judgment device (8) receives wheel load bus signals judgment means (5), described
Air speed bus signals judgment means (6), the hatch door close the output signal of judgment means (7), only when all outputs
When signal is all high level, the upper electric logic judgment device (8) just exports high level, otherwise exports low level.
11. hatch door flight lock systems according to claim 2, it is characterised in that the predetermined airspeed threshold is 80 sections.
12. hatch door flight lock systems according to claim 1, it is characterised in that when the wheel load hard signal (10) is
During high level, it indicates that the aircraft is not on the ground.
13. hatch door flight lock systems according to claim 11, it is characterised in that logic unit (4) tool is locked in the flight
There is a logic judgment device (13), the logic judgment device (13) is for analyzing the defeated of the logical process and control unit (9)
Go out signal and wheel load hard signal (10), only when the wheel load hard signal (10) and the logical process and control unit
(9) when output signal is all high level, the logic judgment device (13) just exports high level, otherwise exports low level.
14. hatch door flight lock systems according to claim 6, it is characterised in that logic unit (4) is locked in the flight to be had
Logic judgment device (13), only when the logic judgment device (13) exports high level, the internal relay (15) is
It is switched on, otherwise, the internal relay (15) is not switched on.
15. hatch door flight lock systems according to claim 1, it is characterised in that the hatch door includes landing gate, service door
Or escape door.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410106296.5A CN103879545B (en) | 2014-03-20 | 2014-03-20 | Cabin door flight lock system for an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410106296.5A CN103879545B (en) | 2014-03-20 | 2014-03-20 | Cabin door flight lock system for an aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103879545A CN103879545A (en) | 2014-06-25 |
| CN103879545B true CN103879545B (en) | 2017-06-09 |
Family
ID=50948742
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410106296.5A Active CN103879545B (en) | 2014-03-20 | 2014-03-20 | Cabin door flight lock system for an aircraft |
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| Country | Link |
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| CN (1) | CN103879545B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443350B (en) * | 2014-11-13 | 2017-10-13 | 中航沈飞民用飞机有限责任公司 | Passenger plane hatch door pressure locking mechanism |
| CN106920300B (en) * | 2017-01-12 | 2024-03-15 | 中国商用飞机有限责任公司 | Access control system of cockpit door, control method thereof and aircraft |
| CN106839957A (en) * | 2017-01-20 | 2017-06-13 | 安徽安凯汽车股份有限公司 | A kind of hatch door position detecting system that function is detected with plug jacket |
| CN108199425B (en) * | 2017-12-20 | 2021-07-16 | 中国航空工业集团公司西安飞行自动控制研究所 | Ground use protection method for emergency power supply of flight control system |
| CN110029893A (en) * | 2019-04-03 | 2019-07-19 | 西安飞机工业（集团）有限责任公司 | A method of it prevents from being opened accidentally aircraft emergency hatch |
| FR3105169B1 (en) * | 2019-12-19 | 2021-12-10 | Latecoere | Safety locking latch aircraft door comprising an electroactive polymer link |
| CN113719215B (en) * | 2021-09-10 | 2022-10-11 | 庆安集团有限公司 | Method and device for operating cabin door |
| CN113942629B (en) * | 2021-11-30 | 2024-06-04 | 中国商用飞机有限责任公司 | Aircraft nacelle plate and aircraft provided with such a nacelle plate |
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| US5984234A (en) * | 1997-10-15 | 1999-11-16 | The Boeing Company | Engine parameter activated airplane exit locking system |
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|---|---|---|---|---|
| US5480109A (en) * | 1993-03-20 | 1996-01-02 | Deutsche Aerospace Airbus Gbmh | System for preventing the automatic opening of an improperly closed and locked aircraft door |
| US5984234A (en) * | 1997-10-15 | 1999-11-16 | The Boeing Company | Engine parameter activated airplane exit locking system |
| CA2421441A1 (en) * | 2002-03-18 | 2003-09-18 | The Boeing Company | Avionic door lock system |
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| Publication number | Publication date |
|---|---|
| CN103879545A (en) | 2014-06-25 |
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Address after: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee after: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute Address before: No.25, Zhangyang Road, Pudong New Area, Shanghai, 200120 Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee before: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute |
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Effective date of registration: 20221021 Address after: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee after: Shanghai Aircraft Design Research Institute Co.,Ltd. Address before: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee before: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute |