CN103879545A - Cabin door flight lock system for aircrafts - Google Patents
Cabin door flight lock system for aircrafts Download PDFInfo
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- CN103879545A CN103879545A CN201410106296.5A CN201410106296A CN103879545A CN 103879545 A CN103879545 A CN 103879545A CN 201410106296 A CN201410106296 A CN 201410106296A CN 103879545 A CN103879545 A CN 103879545A
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Abstract
The invention relates to a cabin door flight lock system for aircrafts. The system comprises a logical processing and controlling unit and a flight lock logical unit, wherein the logical processing and controlling unit generates first cabin door lock signals according to wheel load bus signals, airspeed bus signals and cabin door closing sensor signals; the flight lock logical unit generates second cabin door lock signals according to the first cabin door lock signals and wheel load hardwire signals so as to instruct a cabin door of an aircraft to be set as a locking state or an unlocking state. According to the cabin door flight lock system disclosed by the invention, the cabin door can be prevented from being opened due to misoperation in a flying process of the aircraft while meeting the requirements of normal opening and emergency evacuation of the cabin door; in the meantime, the single point failure can be avoided through the design of the control structure of the cabin door flight lock system, so that the airworthiness clause requirement can be fully met and the safety of the aircraft is guaranteed.
Description
Technical field
The present invention relates to aircraft security field, particularly, the present invention relates to a kind of flight of the hatch door for aircraft lock system.
Background technology
Experiencing after twice cargo door accident nineties, FAA has issued FAR25-114 amendment in 2004, hatch door safety rate has been proposed to very strict requirement.According to the requirement of up-to-date clause, in the hatch door design process of aircraft, must there is measure to prevent that each hatch door from being opened unintentionally by people awing, simultaneously, if these preventive comprise use auxiliary device, these devices and control system thereof must be designed to:
(1) single point failure can not hinder multiple outlets to be opened; With
(2) inefficacy that hinders outlet to open after landing is impossible.
Herein, single point failure refers in the logical process and control unit of hatch door, such as, because the inefficacy (signal of power down or output error etc.) of single sensing device or control setup causes opening the situation of hatch door.
In order to ensure the flight safety of aircraft, need to design a kind of safe flight lock control system, guarantee that aircraft can not opened unintentionally in flight course, meanwhile, can not hinder again normally opening of hatch door, meet performance requriements and safety requirements.
Summary of the invention
The object of the present invention is to provide a kind of safe and reliable hatch door for aircraft flight lock system, its can either prevent hatch door in the flight course of aircraft because maloperation is opened, can not hinder normally opening and the demand of emergency evacuation of hatch door yet, simultaneously, control the design of framework by it and can avoid single point failure, thereby meet fully the requirement of seaworthiness clause and can guarantee the safety of aircraft.
For achieving the above object, the invention provides a kind of flight of the hatch door for aircraft lock system, it is characterized in that comprising logical process and control unit, described logical process and control unit are constructed to generate the first cabin door lock signal according to wheel load bus signals, air speed bus signals, hatch door closure sensor signal; Described hatch door flight lock system also comprises flight lock logical block, described flight lock logical block is constructed to generate the second cabin door lock signal according to described the first cabin door lock signal and wheel load hard signal, is set to locking state or released state to control the hatch door of described aircraft.In the time generating the second cabin door lock signal of the hatch door for controlling aircraft, consider wheel load hard signal by this way, thereby can effectively avoid single point failure, and then improved the demand for security of aircraft.
In a kind of embodiment according to hatch door flight lock system of the present invention, in the time meeting the following conditions: described wheel load bus signals indicates described aircraft not on the ground simultaneously; Described air speed bus signals indicator air speed is greater than predetermined air speed threshold value; And described in described hatch door closure sensor signal designation, hatch door is in closed condition, and described the first cabin door lock signal that described logical process and control unit generate is lock signal on first.Wheel load bus signals, air speed bus signals and hatch door closure sensor in the time generating the first cabin door lock signal, are considered by this way, and it is set need to meet some requirements simultaneously, thereby improve the reliability of the first cabin door lock signal generating.
In a kind of embodiment according to hatch door flight lock system of the present invention, when described the first cabin door lock signal is that on first, lock signal and described wheel load hard signal indicate described aircraft not on the ground time, the second cabin door lock signal generating just indicates the hatch door of described aircraft to be set to locking state.
By analyzing multiple incoming signals, locking of hatch door or release are set according to the flight of the hatch door for aircraft lock system of the present invention, thereby while avoiding high-speed flight aloft, by mistake open described hatch door, and guarantee can normally open described hatch door in the time of ground or in the time that air speed is less than air speed threshold value, this has improved the safety and reliability of described hatch door flight lock system.In addition the problem that, can avoid the hatch door causing due to the single point failure in described logical process and control unit cannot open under normal circumstances in the described wheel load hard signal of the input end of described flight lock logical block.
Accompanying drawing explanation
Fig. 1 shows the functional schematic according to hatch door flight lock system of the present invention; And
Fig. 2 shows the control logic figure according to hatch door flight lock system of the present invention.
The specific embodiment
Figure 1 illustrates the functional schematic according to hatch door flight lock system of the present invention.As can be seen from the figure, this hatch door flight lock system comprises logical process and control unit 9, flight lock logical block 4 and actuating mechanism 16.Wherein, logical process and control unit 9 comprise that wheel load bus signals judgment means 5, air speed bus signals judgment means 6, hatch door close judgment means 7 and the logic judgment means 8 that powers on, and this logical process and control unit 9 receive wheel load bus signals 1, air speed bus signals 2, hatch door closure sensor signal 3 and output the first cabin door lock signal.And wherein, flight lock logical block 4 comprises logic judgment means 13, this flight lock logical block 4 receives the first cabin door lock signal and wheel load hard signal 10 and output the second cabin door lock signal; And wherein, actuating mechanism 16 comprises internal relay 15, o 11 and hatch door mechanism for locking up 12, this actuating mechanism is constructed to be set to locking state or released state according to the hatch door of the second cabin door lock signal aircraft.
The one according to hatch door of the present invention flight lock system preferred embodiment in, wheel load bus signals judgment means 5 is for according to judging that at the wheel load bus signals 1 of the input end of logical process and control unit 9 whether on the ground aircraft, when judging that this aircraft is not on the ground time, this wheel load bus signals judgment means 5 is exported high level, otherwise output low level.The signal being transmitted by bus after the output signal that this wheel load bus signals can be multiple sensors on aircraft is comprehensive by analysis.Air speed bus signals judgment means 6 is for according to judging at the air speed bus signals 2 of the input end of logical process and control unit 9 whether air speed is greater than predetermined air speed threshold value, in the time that air speed is greater than predetermined air speed threshold value, this air speed bus signals judgment means 6 is exported high level, otherwise output low level.Hatch door is closed judgment means 7 for analyzing the hatch door closure sensor signal 3 at the input end of logical process and control unit 9, and in the time judging this hatch door in closed condition, this hatch door is closed judgment means 7 and exported high level, otherwise output low level.This hatch door closure sensor signal 3 is exported by hatch door closure sensor, and in the time detecting that hatch door is in an open position, hatch door closure sensor signal 3 is low level; In the time detecting that hatch door is in the closed position, it is high level.The logic that powers on judgment means 8 is closed the output signal of judgment means 7 for receiving wheel load bus signals judgment means 5, air speed bus signals judgment means 6 and hatch door, only have in the time that all output signals are all high level, this logic judgment means 8 that powers on is just exported high level, otherwise output low level.The output signal of the logic that powers on judgment means 8 is the output signal of logical process and control unit 9, and this output signal is as the incoming signal of flight lock logical block 4.
According to above-mentioned embodiment, when aircraft is on the ground time, the multiple sensors that are for example positioned at alighting gear place can (for example be installed the sensor of tire on alighting gear) in several ways and judge aircraft on the ground, and the output signal of the plurality of sensor is converted to after treatment wheel load bus signals and sends to wheel load bus signals judgment means 5 by the bus in aircraft.Wheel load bus signals judgment means 5 is judged aircraft on the ground by wheel load bus signals in this case, and logic judgment means 8 output low levels that power on.According to follow-up explanation, now hatch door is by release.The advantage of design is to meet the demand of the emergency escape in the time that aircraft is on ground like this.
According to above-mentioned embodiment, the air speed detecting device that is for example positioned at aircraft or is positioned at ground command center records the air speed of aircraft, and this airspeed signal is converted to after treatment air speed bus signals and sends to air speed bus signals judgment means 6 by the bus in aircraft, when air speed bus signals judgment means 6 judges that aircraft is static or when being less than or equal to the speed of air speed threshold value and moving, the logic that powers on judgment means 8 output low levels.According to follow-up explanation, now hatch door is by release.The advantage of design is to meet occupant in the time that aircraft moves with lower speed and jumps the demand that cabin is withdrawn like this.
According to above-mentioned embodiment, when hatch door is during in open mode, the logic that powers on judgment means 8 output low levels.According to follow-up explanation, now hatch door is by release.The advantage of design is to avoid to make in the time that hatch door is opened hatch door flight to lock lock like this.
According to above-mentioned embodiment, by judging that the state of multiple signals is locked hatch door, and the state variation of individual signals just can cause hatch door release.The advantage of design is that the condition that can make hatch door lock is stricter than the condition of hatch door release like this, thereby for example, in the time there is single point failure (the wherein inefficacy of certain judgment means 5,6 or 7), it is possible by the normal work of other judgment means, hatch door normally being opened.
The one according to hatch door of the present invention flight lock system preferred embodiment in, above-mentioned air speed threshold value is 80 joints, it will be understood by those of skill in the art that according to concrete demand for security this air speed threshold design is become to other threshold values, it is also feasible that for example 100 joints wait other values.
The one according to hatch door of the present invention flight lock system preferred embodiment in, in the time that wheel load hard signal 10 is high level, indicate aircraft not on the ground.In this case, logic judgment means 13 is for output signal and the wheel load hard signal 10 of analysis logic processing and control unit 9, only have in the time that the output signal of wheel load hard signal 10 and logical process and control unit 9 is all high level, logic judgment means 13 is just exported high level, otherwise output low level.Wherein, after the output signal that this wheel load hard signal 10 can be multiple sensors on aircraft is comprehensive by analysis by the signal of independent wire transmission.
According to above-mentioned embodiment, when there is the problem of single point failure in logical process and control unit 9 time, for example, in the time that aircraft rest on the ground, when exporting mistakenly high level and cause logical process and control unit 9 to export high level due to wheel load bus signals judgment means 5, or while causing it to export high level due to the mistake powering in logic judgment means 8, can make logic judgment means 13 output low levels by wheel load hard signal 10, according to follow-up explanation, now hatch door is by release.The advantage of design is to avoid the situation that causes hatch door cannot open under normal circumstances because of the single point failure problem occurring in logical process and control unit 9 like this.
The one according to hatch door of the present invention flight lock system preferred embodiment in, only have in the time that logic judgment means 13 is exported high level, internal relay 15 is just switched on, otherwise internal relay 15 is not switched on.Only have in the time that internal relay 15 is switched on, o 11 just powers on by for example 28V power supply 14, otherwise, magnetic solenoid 11 power down.And hatch door mechanism for locking up is constructed in the time that o 11 powers on, hatch door be locked, in the time of o 11 power down, make hatch door release.
The one according to hatch door of the present invention flight lock system preferred embodiment in, hatch door comprises landing gate, service door or emergency door.
Figure 2 illustrates the control logic figure according to hatch door flight lock system of the present invention.In step S21, judge whether wheel load bus signals indicates aircraft not on the ground, in step S22, judge whether air speed bus signals indicates the air speed of aircraft to be greater than 80 joints.In step S23, judge whether hatch door closure sensor signal indicates hatch door in closed condition, if judge to be all "Yes" in S21, S22, S23, in step S24, be judged to be "Yes"; If be judged to be arbitrarily "No" in step S21, S22, S23, in step S24, be judged to be "No".In step S25, judge whether wheel load hard signal indicates aircraft not on the ground.In step S26, if judging in S24 and S25 is all "Yes", enter in step S27, screw actuator powers on and hatch door is locked; If be judged to be arbitrarily "No" in S24 and S25, enter in step S28 screw actuator power down and hatch door release.
By analyzing multiple incoming signals, locking of hatch door or release are set according to the flight of the hatch door for aircraft lock system of the present invention, thereby while avoiding high-speed flight aloft, by mistake open described hatch door, and guarantee can normally open described hatch door in the time of ground or in the time that air speed is less than air speed threshold value, this has improved the safety and reliability of described hatch door flight lock system.In addition the problem that, can avoid the hatch door causing due to the single point failure in described logical process and control unit cannot open under normal circumstances in the described wheel load hard signal of the input end of described flight lock logical block.
Although more than described the specific embodiment of the present invention, those skilled in the art can make various changes and modifications within the scope of the appended claims.
Claims (16)
1. for a hatch door flight lock system for aircraft, it is characterized in that, comprising:
Logical process and control unit (9), it is constructed to generate the first cabin door lock signal according to wheel load bus signals (1), air speed bus signals (2), hatch door closure sensor signal (3);
Flight lock logical block (4), it is constructed to generate the second cabin door lock signal according to described the first cabin door lock signal and wheel load hard signal (10), is set to locking state or released state to control the hatch door of described aircraft.
2. hatch door flight lock system according to claim 1, is characterized in that, in the time meeting the following conditions simultaneously:
Described wheel load bus signals (1) indicates described aircraft not on the ground;
Described air speed bus signals (2) indicator air speed is greater than predetermined air speed threshold value; And
Described hatch door closure sensor signal (3) indicates described hatch door in closed condition,
Described the first cabin door lock signal that described logical process and control unit (9) generate is lock signal on first.
3. hatch door flight lock system according to claim 1, is characterized in that, in the time meeting the following conditions:
Described wheel load bus signals (1) indicate described aircraft on the ground or
Described air speed bus signals (2) indicator air speed be less than predetermined air speed threshold value or
Described hatch door closure sensor signal (3) indicates described hatch door in open mode,
Described the first cabin door lock signal that described logical process and control unit (9) generate is the first unlocking signal.
4. hatch door flight lock system according to claim 2, it is characterized in that, indicate described aircraft not on the ground time when described wheel load hard signal (10), the hatch door that the second cabin door lock signal generating is just controlled described aircraft is set to locking state.
5. hatch door flight lock system according to claim 1, it is characterized in that, in the time that described wheel load hard signal (10) indicates described aircraft on the ground, the hatch door of the described aircraft of the second cabin door lock signal designation generating is set to released state.
6. hatch door flight lock system according to claim 1, it is characterized in that, described hatch door flight lock system also comprises actuating mechanism (16), and described actuating mechanism is constructed to be set to locking state or released state according to the hatch door of the described aircraft of described the second cabin door lock signal.
7. hatch door flight lock system according to claim 6, it is characterized in that, described actuating mechanism (16) comprises internal relay (15), o (11) and hatch door mechanism for locking up (12), described hatch door mechanism for locking up is constructed in the time that described o (11) powers on, described hatch door be locked, and makes described hatch door release in the time of described o (11) power down.
8. hatch door flight lock system according to claim 1, it is characterized in that, described logical process and control unit (9) have for judging whether wheel load bus signals judgment means (5) on the ground of described aircraft, when described wheel load bus signals judgment means (5) judges that by analyzing described wheel load bus signals (1) described aircraft is not on the ground time, export high level, otherwise output low level.
9. hatch door flight lock system according to claim 1, it is characterized in that, described logical process and control unit (9) have for judging whether described air speed is greater than the air speed bus signals judgment means (6) of described predetermined air speed threshold value, in the time that described air speed bus signals judgment means (6) judges that by analyzing described air speed bus signals (2) described air speed is greater than described predetermined air speed threshold value, export high level, otherwise output low level.
10. hatch door flight lock system according to claim 1, it is characterized in that, the hatch door that described logical process and control unit (9) have for analyzing described hatch door closure sensor signal (3) is closed judgment means (7), only have and close judgment means (7) by analyzing described hatch door closure sensor signal (3) while judging described hatch door in closed condition when described hatch door, just export high level, otherwise output low level.
11. according to the hatch door flight lock system described in any one in claim 1 to 10, it is characterized in that, described logical process and control unit (9) also have the logic of powering on judgment means (8), the described logic judgment means (8) that powers on receives described wheel load bus signals judgment means (5), described air speed bus signals judgment means (6), described hatch door is closed the output signal of judgment means (7), only have in the time that all described output signals are all high level, the described logic judgment means (8) that powers on is just exported high level, otherwise output low level.
12. hatch door flight lock systems according to claim 1, is characterized in that described predetermined air speed threshold value is 80 joints.
13. hatch door flight lock systems according to claim 1, is characterized in that, in the time that described wheel load hard signal (10) is high level, indicate described aircraft not on the ground.
14. hatch door flight lock systems according to claim 12, it is characterized in that, described flight lock logical block (4) has logic judgment means (13), described logic judgment means (13) is for analyzing output signal and the wheel load hard signal (10) of described logical process and control unit (9), only have in the time that the output signal of described wheel load hard signal (10) and described logical process and control unit (9) is all high level, described logic judgment means (13) is just exported high level, otherwise output low level.
15. hatch door flight lock systems according to claim 6, it is characterized in that, described flight lock logical block (4) has logic judgment means (13), only have in the time of described logic judgment means (13) output high level, described internal relay (15) is just switched on, otherwise described internal relay (15) is not switched on.
16. hatch door flight lock systems according to claim 1, is characterized in that, described hatch door comprises landing gate, service door or emergency door.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410106296.5A CN103879545B (en) | 2014-03-20 | 2014-03-20 | For the hatch door flight lock system of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410106296.5A CN103879545B (en) | 2014-03-20 | 2014-03-20 | For the hatch door flight lock system of aircraft |
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| CN103879545A true CN103879545A (en) | 2014-06-25 |
| CN103879545B CN103879545B (en) | 2017-06-09 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104443350A (en) * | 2014-11-13 | 2015-03-25 | 中航沈飞民用飞机有限责任公司 | Pressure locking mechanism of passenger plane cabin door |
| 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 |
| CN106920300A (en) * | 2017-01-12 | 2017-07-04 | 中国商用飞机有限责任公司 | The gate control system and its control method of a kind of cockpit door, and aircraft |
| CN108199425A (en) * | 2017-12-20 | 2018-06-22 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of flight control system stand-by power supply ground uses guard method |
| 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 |
| WO2021122567A1 (en) * | 2019-12-19 | 2021-06-24 | Latecoere | Aircraft door with a safety latch comprising an electroactive polymer link |
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443350A (en) * | 2014-11-13 | 2015-03-25 | 中航沈飞民用飞机有限责任公司 | Pressure locking mechanism of passenger plane cabin door |
| CN106920300A (en) * | 2017-01-12 | 2017-07-04 | 中国商用飞机有限责任公司 | The gate control system and its control method of a kind of cockpit door, and aircraft |
| 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 |
| CN108199425A (en) * | 2017-12-20 | 2018-06-22 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of flight control system stand-by power supply ground uses guard method |
| 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 |
| WO2021122567A1 (en) * | 2019-12-19 | 2021-06-24 | Latecoere | Aircraft door with a safety latch comprising an electroactive polymer link |
| FR3105169A1 (en) * | 2019-12-19 | 2021-06-25 | Latecoere | Safety locking latch aircraft door comprising an electroactive polymer link |
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
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