CN112327686A - Advanced airplane cabin door centralized management system - Google Patents
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- CN112327686A CN112327686A CN202011163193.4A CN202011163193A CN112327686A CN 112327686 A CN112327686 A CN 112327686A CN 202011163193 A CN202011163193 A CN 202011163193A CN 112327686 A CN112327686 A CN 112327686A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0428—Safety, monitoring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1423—Passenger doors
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
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Abstract
The invention discloses an advanced airplane cabin door centralized management system, which is based on a multi-electric airplane technology, an electromechanical integrated management technology and a bus technology and comprises a cabin door centralized controller, a cabin door actuating subsystem, a cabin door control panel and a cabin door system bus, wherein the cabin door centralized controller, the cabin door actuating subsystem and the cabin door control panel are interconnected through the cabin door system bus. The cabin door actuating subsystem comprises all electric cabin door systems on the airplane and realizes electric operation of the cabin doors in an electromechanical actuating mode; the cabin door centralized controller can realize centralized control and management on the cabin door actuating subsystem, and simultaneously accesses the public equipment management system to realize electromechanical integrated management; the cabin door control panel is a visual part for realizing man-machine interaction of the whole cabin door comprehensive management system, and an operator can operate the cabin door actuator through the control panel and learn the current state of the cabin door system. The method can realize the automatic operation and centralized management of the advanced airplane door.
Description
Technical Field
The invention belongs to the technical field of multi-electric airplanes, and particularly relates to a cabin door management system.
Background
The multiple electrical technology and even the full electrical technology are well-known development trends of the aircraft, the multiple electrical technology of the aircraft has a series of advantages of simple structure, light weight, high reliability, good maintainability, low use cost, simple on-board interfaces, high energy utilization rate, less pollution emission, easy energy transmission and management and the like, and the multiple electrical technology is applied and verified on the aircraft with the models of F-35, B787, A380 and the like at present.
However, the automation degree of the prior multi-electric airplane on the cabin door system is not high, the passenger cabin doors of advanced civil aircrafts such as B787, A380 and the like still adopt a manual opening/closing operation mode, and the working load of service personnel is increased to a certain extent; due to the large area and weight of cargo doors, more civil aircraft have cancelled the manual operation mode, but the mode of hydraulic actuation is used instead, which obviously does not accord with the development trend of multi-electric aircraft.
On the other hand, the integrated management of onboard public equipments (referred to as electromechanical integrated management in China), that is, the whole public equipment system is regarded as a whole, and the technology such as data bus and multi-processor is adopted to implement unified management, which is the development direction of onboard equipment management. Currently, aircraft door systems do not form an integral unit that can be incorporated into a common equipment management system, and there is no dedicated controller to perform the management of the entire aircraft door system.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an advanced airplane cabin door centralized management system which is based on an electric airplane technology, an electromechanical integrated management technology and a bus technology and consists of a cabin door centralized controller, a cabin door actuating subsystem, a cabin door control panel and a cabin door system bus, wherein the cabin door centralized controller, the cabin door actuating subsystem and the cabin door control panel are interconnected through the cabin door system bus. The cabin door actuating subsystem comprises all electric cabin door systems on the airplane and realizes electric operation of the cabin doors in an electromechanical actuating mode; the cabin door centralized controller can realize centralized control and management on the cabin door actuating subsystem, and simultaneously accesses the public equipment management system to realize electromechanical integrated management; the cabin door control panel is a visual part for realizing man-machine interaction of the whole cabin door comprehensive management system, and an operator can operate the cabin door actuator through the control panel and learn the current state of the cabin door system. The method can realize the automatic operation and centralized management of the advanced airplane door.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an advanced airplane cabin door centralized management system comprises a cabin door centralized controller, n cabin door actuating subsystems, m cabin door control panels and a cabin door system bus; the cabin door centralized controller, the n cabin door actuating subsystems and the m cabin door control panels are all connected to a cabin door system bus;
sending a control command to the cabin door centralized controller through a cabin door system bus by operating the cabin door control panel; after the cabin door integrated controller receives the control instruction, the cabin door actuating subsystem is controlled through the cabin door system bus, and the control of the airplane cabin door is realized;
the cabin door centralized controller comprises a centralized control bus communication module, a centralized control CPU, a logic analysis module and a control law module; the centralized control bus communication module comprises a first sending submodule and a first receiving submodule, and is connected with the cabin door system bus and used for receiving and sending information; the centralized control CPU is respectively connected with the centralized control bus communication module, the logic analysis module and the control law module, when the first receiving submodule of the centralized control bus communication module receives data, if the data source is the cabin door control panel, the centralized control CPU judges that an operator has an operation demand on the airplane cabin door, and the logic analysis module judges the validity of a control instruction sent by the cabin door control panel: when the control instruction sent by the cabin door control panel is judged to be effective, the CPU is controlled in a centralized manner to enable the control law module, and the cabin door actuating subsystem is controlled to act by the control law module; otherwise, when the control instruction sent by the cabin door control panel is judged to be invalid, the centralized control CPU does not enable the control law module;
the cabin door actuator subsystem comprises a cabin door control bus communication module, a cabin door control CPU, a PWM module, a motor driving module, an electromechanical actuator and a sensor signal processing module; the electromechanical actuator comprises an electric motor; the cabin door control bus communication module comprises a second sending submodule and a second receiving submodule, and is respectively connected with the cabin door system bus and the cabin door control CPU and used for receiving and sending information; the cabin door control CPU, the PWM module, the motor driving module and the electromechanical actuator are sequentially connected, the cabin door control CPU sends a signal, the PWM module modulates the signal and then triggers the motor driving module to work to drive the motor to rotate so as to drive the cabin door to act;
the sensor signal processing module comprises a motor sensor signal processing submodule and a proximity sensor signal processing submodule, wherein the motor sensor signal processing submodule acquires current, speed and position information of a motor, and the proximity sensor signal processing submodule acquires position information of an airplane cabin door; and the information acquired by the motor sensor signal processing submodule and the proximity sensor signal processing submodule is sent to a cabin door control CPU, and then is sent to a cabin door system bus by the second sending submodule and acquired by the cabin door centralized controller to form a feedback system.
Preferably, the centralized controller of the hatches is connected to a common device management system bus of the aircraft, and uploads or obtains status information of the hatches.
Preferably, the centralized hatch door controller further comprises a fault diagnosis module and a fault-tolerant control module; when any cabin door actuating subsystem fails, the fault diagnosis module can analyze the fault position according to the state information of the failed cabin door actuating subsystem and feed the fault position back to a cabin door control CPU; the fault-tolerant control module corrects the consequence generated by the fault of the cabin door actuating subsystem by combining the fault state of the cabin door actuating subsystem, the output of the logic analysis module and the output of the control law module, and completes the fault-tolerant control of the cabin door actuating subsystem.
Preferably, n ≧ m.
Preferably, the n door actuating subsystems are connected by a door system bus without direct connection.
Preferably each door actuation subsystem comprises a plurality of electromechanical actuators for effecting different movements of the door.
Preferably, the different actions of the door include, but are not limited to, latching, flight locking, door body opening/closing.
Due to the adoption of the advanced airplane cabin door centralized management system, the following beneficial effects are brought:
1. the problem that the cabin door is low in efficiency due to the fact that the airplane is opened and closed through manual or hydraulic actuation can be solved, and the adopted electric operation mode also meets the development trend of future scientific and technological automation and intellectualization;
2. the cabin door centralized controller is used for carrying out centralized management on the cabin doors, so that the electromechanical comprehensive management of the whole machine layer is favorably realized; one cabin door centralized controller replaces a plurality of controllers under the traditional architecture, so that the economic cost is reduced;
3. the whole system is highly centralized to the cabin door centralized controller in function, and the fault points of the system are greatly reduced; compared with the traditional airplane framework, the cabin door integrated controller can be installed in an airplane with a better working environment, so that the influence of electromagnetic interference on a cabin door system is reduced; proximity sensors mounted on the cabin door in a large number can perform proximity processing through a corresponding cabin door control CPU, so that a large number of routing cables are reduced, and the problems of signal attenuation and electromagnetic interference caused by overlong cables are solved.
Drawings
Fig. 1 is a schematic diagram of the centralized management system architecture of the hatchway of the present invention.
Fig. 2 is a schematic diagram of an aircraft common equipment management system architecture according to the present invention.
FIG. 3 is a schematic view of the cabin door actuation subsystem according to the present invention.
Fig. 4 is a functional structure diagram of the centralized controller of the hatch door of the invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
As shown in FIG. 1, the present invention provides an advanced airplane door centralized management system, which comprises
An advanced airplane door centralized management system comprises a door centralized controller 200, n door actuating subsystems 201, m door control panels 203 and a door system bus 202; the hatch centralized controller 200, the n hatch actuation subsystems 201 and the m hatch control panels 203 are all connected to a hatch system bus 202;
sending control commands to the hatch centralized controller 200 via the hatch system bus 202 by manipulating the hatch control panel 203; after receiving the control instruction, the cabin door centralized controller 200 controls the cabin door actuator subsystem 201 through the cabin door system bus 202 to control the airplane cabin door;
the hatch centralized controller 200 comprises a centralized control bus communication module 400, a centralized control CPU401, a logic analysis module 402 and a control law module 403; the centralized control bus communication module 400 comprises a first sending submodule and a first receiving submodule, and the centralized control bus communication module 400 is connected with the cabin door system bus 202 and used for receiving and sending information; the centralized control CPU401 is connected to the centralized control bus communication module 400, the logic analysis module 402, and the control law module 403, respectively, when the first receiving sub-module of the centralized control bus communication module 400 receives data, if the data source is the cabin door control panel 203, the centralized control CPU401 determines that an operator has an operation demand for an aircraft cabin door, and the logic analysis module 402 determines validity of a control instruction sent by the cabin door control panel 203: when the control instruction sent by the cabin door control panel 203 is judged to be valid, the centralized control CPU400 enables the control law module 403, and the control law module 403 controls the cabin door actuation subsystem 201 to actuate; otherwise, when the control instruction sent by the cabin door control panel 203 is judged to be invalid, the centralized control CPU400 does not enable the control law module;
the door actuation subsystem 201 comprises a door control bus communication module 300, a door control CPU301, a PWM module 302, a motor drive module 303, an electromechanical actuator 304 and a sensor signal processing module 305; the electromechanical actuator 304 comprises an electric motor; the hatch door control bus communication module 300 comprises a second sending submodule and a second receiving submodule, and the hatch door control bus communication module 300 is respectively connected with the hatch door system bus 202 and the hatch door control CPU301 and is used for receiving and sending information; the cabin door control CPU301, the PWM module 302, the motor driving module 303 and the electromechanical actuator 304 are sequentially connected, the cabin door control CPU301 sends out signals, the PWM module 302 modulates the signals and then triggers the motor driving module 303 to work to drive the motor to rotate so as to drive the cabin door to act;
the sensor signal processing module 305 comprises a motor sensor signal processing submodule and a proximity sensor signal processing submodule, wherein the motor sensor signal processing submodule acquires current, speed and position information of a motor, and the proximity sensor signal processing submodule acquires position information of an airplane door; the information obtained by the motor sensor signal processing submodule and the proximity sensor signal processing submodule is sent to the cabin door control CPU301, then sent to the cabin door system bus 202 by the second sending submodule and obtained by the cabin door centralized controller 200, and a feedback system is formed.
Preferably, the hatch centralized controller 200 is connected to a common device management system bus 101 of the aircraft, and uploads or acquires status information of the aircraft on the status of the hatches.
Preferably, the hatch centralized controller 200 further comprises a fault diagnosis module 404 and a fault tolerant control module 405; when any cabin door actuating subsystem 201 fails, the fault diagnosis module 404 can analyze the fault position according to the state information of the failed cabin door actuating subsystem 201 and feed the fault position back to the cabin door control CPU 301; the fault-tolerant control module 405 corrects the consequences of the failure of the door actuation subsystem 201 by combining the failure state of the door actuation subsystem 201, the output of the logic analysis module 402 and the output of the control law module 403, and completes the fault-tolerant control of the door actuation subsystem 201.
Preferably, n ≧ m.
Preferably, the n door actuators 201 are connected by a door system bus, and are not directly connected.
Preferably, each door actuation subsystem 201 comprises a plurality of electromechanical actuators 304 for effecting different movements of the door.
Preferably, the different actions of the door include, but are not limited to, latching, flight locking, door body opening/closing.
The specific embodiment is as follows:
fig. 2 is a schematic diagram of the architecture of a common equipment management system of an aircraft, wherein common equipment refers to a general term of systems responsible for continuous and safe flight of the aircraft, and does not include avionics systems which are indispensable for completing critical tasks and systems related to flight control and engine control. Each subsystem under the public equipment management system realizes information interaction through the public equipment management system bus 101, and as for the airplane cabin door, the cabin door system 102 does not belong to an avionics system and does not participate in flight control, the cabin door system accesses the public equipment management system bus and receives management and scheduling of the public equipment management computer 100.
The centralized management system for the hatches comprises a centralized controller for the hatches, a hatche actuating subsystem, a hatche control panel and a hatche system bus, and the structure of the centralized management system is shown in fig. 1. The cabin door centralized management system architecture is similar to the common equipment management system architecture, and is based on a bus form, each subsystem is used as a node of the system bus, the interconnection mode among the nodes is cancelled, a large number of IO cables are saved, the CPU of the subsystem only needs to transmit and receive data through the cabin door system bus 202, and the task load of the subsystem on data communication is greatly reduced. The core of the centralized management system for the hatches is the centralized controller 200 for the hatches, each actuating system 201 of the hatches in the centralized management system can be directly controlled by the centralized controller for the hatches through the hatches system bus, the control process of each hatch actuator is started by operating the corresponding control panel 203, since one control panel can control a plurality of hatch actuating subsystems, the total number m of the control panels is smaller than and equal to the total number n of the actuating systems for the hatches.
The cabin door actuation subsystem in the cabin door centralized management system adopts an electromechanical actuation mode, and the structure of the cabin door actuation subsystem is shown in fig. 3. Different operations are possible for the same door, such as latching, flight lock operation, door switch operation, etc., and thus the same door actuator subsystem requires a plurality of electromechanical actuators, each of which is similar in structure, and the door actuation system of figure 3 is illustrated with one electromechanical actuator as an example.
The cabin door actuating subsystem comprises a cabin door control bus communication module, a cabin door control CPU, a PWM module, a motor driving module, an electromechanical actuator and a sensor signal processing module. The core of the electromechanical actuator is an electric motor 304, the cabin door centralized controller and the cabin door control CPU301 are generally used as controllers of the electromechanical actuator, and the control over the electric motor is completed by the cabin door centralized controller and the cabin door control CPU together. If a current closed loop exists in the control of the motor, the current loop is required to have higher real-time performance and short control period in the control of the motor, so that the current loop control law exists in a cabin door control CPU at the moment. The control information of the cabin door centralized controller is acquired from a cabin door system bus by a receiving submodule of the cabin door control bus communication module 300, a cabin door CPU performs necessary processing on the control information, then the PWM module 302 triggers the motor driving module 303 to work, the motor driving module drives the motor to rotate, and along with the rotation of the motor, the electromechanical actuator can drive the cabin door mechanism to act, so that the electric operation of the cabin door is completed. The current, speed, position and other information of the motor are obtained through the motor sensor, the position information of the cabin door mechanism is obtained through the proximity sensor, two sensing signals are respectively processed by the motor sensor signal processing submodule and the proximity sensor signal processing submodule in the sensor signal processing module 305, and finally are sent to the bus through the sending submodule of the bus communication module after being collected by the cabin door CPU for the cabin door centralized controller to obtain, so that closed-loop feedback is formed.
After the cabin door centralized controller acquires the state of the cabin door actuating subsystem, the cabin door centralized controller completes control over the cabin door actuating subsystem after a series of processing, and a functional block diagram of the cabin door centralized controller is shown in fig. 4. Similar to fig. 3, the door centralized controller should have a plurality of identical sub-modules to accomplish the control of the entire cabin door actuation system, and the module shown in fig. 4 is a typical example of a certain type of module.
The hatch centralized controller comprises a centralized control bus communication module 400, the communication with the hatch system bus is completed by the hatch system bus interface of the centralized control bus communication module, and the centralized control bus communication module has two sub-modules of sending and receiving. The cabin door centralized controller is required to communicate with the cabin door centralized management system, and also communicate with a common equipment management system bus (UMS bus), for example, the state of the cabin door system affects the enabling of the environmental control pressurization system and the enabling of the cargo compartment lighting system, so that the cabin door centralized controller is required to upload the state of the cabin door system to the common equipment management system bus in time; on the other hand, the status of the cabin door system, such as the status of the flight lock, may be affected by the wheel load signal, the airspeed signal, etc. of the aircraft, so that the cabin door centralized controller needs to acquire these data from the common device management system bus; in addition to these two points, the warning information of the door system needs to be communicated to the driver and maintenance personnel, and therefore the door system also has a need to communicate with the upper system.
The cabin door centralized controller receives data on the bus through a cabin door system bus interface, the data source can be judged, the judgment process is completed by the judgment of a cabin door CPU according to a communication protocol of a formulated bus application layer, when the cabin door CPU judges that the data comes from a control panel, the judgment that an operator has an operation demand on a cabin door system is judged, the cabin door centralized controller can combine an instruction of the control panel and the state of the cabin door system at the moment, the judgment on the instruction validity of the control panel is completed through a logic analysis module 402, once the control instruction issued by the control panel is judged to be valid, a control law module 403 can be enabled, and the operation process of a corresponding cabin door actuating subsystem is started at the moment. In the operation process of the control cabin door actuating subsystem, the cabin door control CPU can directly call the control law module to complete the process control of the cabin door actuator.
The hatch centralized controller has a health management function, which is performed by a fault diagnosis module 404 and a fault tolerant control module 405. For the fault diagnosis module, when a certain cabin door actuating system breaks down, the fault position can be analyzed according to the state information of the cabin door actuating subsystem and fed back to the CPU. If the fault exists in the operation process of the cabin door actuating subsystem, the fault diagnosis result can enable the fault-tolerant control module, and at the moment, the fault-tolerant control module corrects the result generated by the fault by combining the fault state of the cabin door actuating system, the result of logic analysis and the output of the control law, so that the fault-tolerant control of the cabin door actuating system is completed. For example, if a certain hatch door approach sensor fails, it generates an erroneous approach or distance signal, and if the erroneous signal is obtained by the hatch door centralized controller in a non-operating state of the hatch door, the sensor may be analyzed to generate fault diagnosis information through a certain logical relationship, and at this time, the fault diagnosis module mainly completes the health management of the hatch door system; in another case, if the fault of the proximity sensor is not shown in the non-operation condition of the cabin door actuating system but is influenced in the operation condition of the actuating system, the fault diagnosis module is required to find or predict that the fault of the sensor exists in time, the fault-tolerant control module starts to operate at the moment, and additional compensation measures are started to enable the cabin door actuating system to execute the operation task as normal as possible, so that the normal operation of the cabin door actuating system at the current time is not influenced, and meanwhile, after the operation is finished, fault information is reported to finish the health management of the cabin door system.
Claims (7)
1. An advanced airplane cabin door centralized management system is characterized by comprising a cabin door centralized controller, n cabin door actuating subsystems, m cabin door control panels and a cabin door system bus; the cabin door centralized controller, the n cabin door actuating subsystems and the m cabin door control panels are all connected to a cabin door system bus;
sending a control command to the cabin door centralized controller through a cabin door system bus by operating the cabin door control panel; after the cabin door integrated controller receives the control instruction, the cabin door actuating subsystem is controlled through the cabin door system bus, and the control of the airplane cabin door is realized;
the cabin door centralized controller comprises a centralized control bus communication module, a centralized control CPU, a logic analysis module and a control law module; the centralized control bus communication module comprises a first sending submodule and a first receiving submodule, and is connected with the cabin door system bus and used for receiving and sending information; the centralized control CPU is respectively connected with the centralized control bus communication module, the logic analysis module and the control law module, when the first receiving submodule of the centralized control bus communication module receives data, if the data source is the cabin door control panel, the centralized control CPU judges that an operator has an operation demand on the airplane cabin door, and the logic analysis module judges the validity of a control instruction sent by the cabin door control panel: when the control instruction sent by the cabin door control panel is judged to be effective, the CPU is controlled in a centralized manner to enable the control law module, and the cabin door actuating subsystem is controlled to act by the control law module; otherwise, when the control instruction sent by the cabin door control panel is judged to be invalid, the centralized control CPU does not enable the control law module;
the cabin door actuator subsystem comprises a cabin door control bus communication module, a cabin door control CPU, a PWM module, a motor driving module, an electromechanical actuator and a sensor signal processing module; the electromechanical actuator comprises an electric motor; the cabin door control bus communication module comprises a second sending submodule and a second receiving submodule, and is respectively connected with the cabin door system bus and the cabin door control CPU and used for receiving and sending information; the cabin door control CPU, the PWM module, the motor driving module and the electromechanical actuator are sequentially connected, the cabin door control CPU sends a signal, the PWM module modulates the signal and then triggers the motor driving module to work to drive the motor to rotate so as to drive the cabin door to act;
the sensor signal processing module comprises a motor sensor signal processing submodule and a proximity sensor signal processing submodule, wherein the motor sensor signal processing submodule acquires current, speed and position information of a motor, and the proximity sensor signal processing submodule acquires position information of an airplane cabin door; and the information acquired by the motor sensor signal processing submodule and the proximity sensor signal processing submodule is sent to a cabin door control CPU, and then is sent to a cabin door system bus by the second sending submodule and acquired by the cabin door centralized controller to form a feedback system.
2. The advanced airplane door centralized management system according to claim 1, wherein said door centralized controller is connected to a common device management system bus of the airplane to upload or obtain status information of the doors.
3. The advanced aircraft door centralized management system according to claim 1, wherein said door centralized controller further comprises a fault diagnosis module and a fault tolerant control module; when any cabin door actuating subsystem fails, the fault diagnosis module can analyze the fault position according to the state information of the failed cabin door actuating subsystem and feed the fault position back to a cabin door control CPU; the fault-tolerant control module corrects the consequence generated by the fault of the cabin door actuating subsystem by combining the fault state of the cabin door actuating subsystem, the output of the logic analysis module and the output of the control law module, and completes the fault-tolerant control of the cabin door actuating subsystem.
4. The advanced airplane door centralized management system of claim 1, wherein n is greater than or equal to m.
5. The advanced aircraft door centralized management system of claim 1, wherein said n door actuation subsystems are connected by means of a door system bus without direct connection.
6. An advanced aircraft door centralized management system according to claim 1, wherein each door actuation subsystem comprises a plurality of electromechanical actuators for effecting different actions on the doors.
7. An advanced aircraft door centralized management system according to claim 1, wherein the different actions of the doors include but are not limited to latching, flight locking, door body opening/closing.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
| CN114995225A (en) * | 2022-05-25 | 2022-09-02 | 兰州万里航空机电有限责任公司 | Controller based on cockpit cover operating device |
| CN115199154A (en) * | 2022-07-04 | 2022-10-18 | 贵州航天天马机电科技有限公司 | Pneumatic drive ejecting device execution system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19730918A1 (en) * | 1997-07-18 | 1999-01-21 | Daimler Benz Aerospace Airbus | Aircraft cabin door locking system |
| CN103967373A (en) * | 2014-05-05 | 2014-08-06 | 中国商用飞机有限责任公司 | Airplane power-driven cabin door safety control system and control method thereof |
| CN104326092A (en) * | 2014-09-05 | 2015-02-04 | 哈尔滨飞机工业集团有限责任公司 | Cabin door alarm control system |
| CN107654158A (en) * | 2017-10-17 | 2018-02-02 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft door electric control system |
-
2020
- 2020-10-27 CN CN202011163193.4A patent/CN112327686B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19730918A1 (en) * | 1997-07-18 | 1999-01-21 | Daimler Benz Aerospace Airbus | Aircraft cabin door locking system |
| CN103967373A (en) * | 2014-05-05 | 2014-08-06 | 中国商用飞机有限责任公司 | Airplane power-driven cabin door safety control system and control method thereof |
| CN104326092A (en) * | 2014-09-05 | 2015-02-04 | 哈尔滨飞机工业集团有限责任公司 | Cabin door alarm control system |
| CN107654158A (en) * | 2017-10-17 | 2018-02-02 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft door electric control system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
| CN114995225A (en) * | 2022-05-25 | 2022-09-02 | 兰州万里航空机电有限责任公司 | Controller based on cockpit cover operating device |
| CN115199154A (en) * | 2022-07-04 | 2022-10-18 | 贵州航天天马机电科技有限公司 | Pneumatic drive ejecting device execution system |
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