An aircraft door control system and control assembly

Abstract

The application belongs to the technical field of aircraft component and assembly design and manufacturing, and discloses an aircraft cabin door control system, which comprises a microprocessor module, an interface circuit module, a driving module, a cabin door signal logic control module and a self-detection module, the microprocessor unit comprises an A / D conversion module and a data processing and logic judgment unit, the interface circuit module comprises a plurality of aircraft cabin door position sensors and a slide pre-position inductance sensor signal, the driving module comprises a door driving, a slide driving and a fire alarm driving, and the self-detection module comprises a fault detector. The application provides the collection, transmission, processing, position state indication and cabin door abnormal alarm of the aircraft cabin door position sensor signal by designing the aircraft cabin door signal control system and control assembly, simultaneously provides the BITE self-detection function of the aircraft cabin door control system, reduces the operation failure probability of the crew, and improves the safety during flight.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft component and assembly design and manufacturing, and particularly relates to an aircraft cabin door control system and a control assembly. BACKGROUND

[0002] In the prior art, researches on aircraft cabin door systems mainly focus on cabin door structures, door lock mechanisms and other cabin door structure aspects, and researches on how aircraft cabin door sensor signals are detected, state indication and state abnormality warning under the control of aircraft cabin door assembly are less. As an important part of aircraft structure, the cabin door is directly related to the flight safety of the aircraft and the life safety of the crew and passengers, and the aircraft cabin door control assembly plays a central control role in the aircraft cabin door control system, and is directly related to the opening and closing state of the cabin door, sealing failure, state indication failure and false action alarm, and the current research lacks comprehensive analysis on cabin door logic signal processing.

[0003] Meanwhile, the main defect of the prior art is that researches are mainly focused on aircraft cabin door structures, door lock mechanisms and other structures, and lack of researches on cabin door signal logic control, state indication and abnormal state alarm.

[0004] Therefore, by designing the control logic of the aircraft cabin door and the function of the control system, the cabin door control assembly can give a real state display according to the actual state of the cabin door after receiving the data transmitted by different sensors, and can realize automatic alarm of the cabin door under abnormal signals, give abnormal state information indication, timely remind the crew to operate or maintain the cabin door normally, improve the fault repair probability, and improve the safety during flight. SUMMARY

[0005] The application aims at the above problems, and provides an aircraft cabin door control system and a control assembly, which has the advantages of reducing the probability of operation errors of the crew and improving the safety during flight.

[0006] To achieve the above object, the application provides the following technical scheme: an aircraft cabin door control system, comprising a microprocessor module, an interface circuit module, a driving module, a cabin door signal logic control module and a self-detection module, the microprocessor unit comprising an A / D conversion module and a data processing and logic judgment unit;

[0007] The interface circuit module comprises a plurality of aircraft cabin door position sensors and a slide ladder pre-position inductance sensor signal;

[0008] The driving module comprises a door driving, a slide ladder driving and a fire alarm driving;

[0009] The self-detection module comprises a fault detector;

[0010] And the microprocessor module, interface circuit module, drive module, hatch signal logic control module and self-detection module are electrically connected with each other.

[0011] Preferably, the aircraft hatch position sensor and the slide pre-position inductance sensor are both eddy current proximity sensors.

[0012] Preferably, the interface circuit module further comprises a power module, wherein the power module is divided into a digital power supply and an analog power supply.

[0013] Preferably, the analog power supply and the digital power supply both use a 5V voltage stabilizer to provide working voltage.

[0014] Preferably, the hatch position sensor uses a DC 28V voltage with a maximum output current of 5A, and the driving power supply is a 28V independent power supply independent of the power module.

[0015] The method comprises the following steps:

[0016] S1, a 12-bit A / D converter is selected, and the sampling clock frequency of the control system is 1MHz;

[0017] S2, a microprocessor is used as a data processing and logic judgment unit to meet the requirement of quickly reading data after each AD sampling is completed, and to complete the processing requirement of the control system;

[0018] S3, the inductance signal of the proximity hatch position eddy current proximity sensor is collected to provide an inductance value corresponding to the actual position of the hatch, and threshold value judgment is performed on the inductance value and the on-off inductance of the hatch, and finally a logic judgment value of the on-off state of the hatch is given;

[0019] S4, a solid-state drive relay is directly controlled by the microprocessor chip, and the output end of the solid-state relay controls the hatch actuator and the controller to complete the hatch on-off control, the slide pre-position control and the hatch indication function;

[0020] S5, according to the inductance value collected by the microprocessor from the hatch position proximity sensor, the on-off state threshold value of the hatch position is set, the microprocessor compares the collected inductance value with the on-off threshold value, and when the on-off state threshold value is exceeded, the microprocessor gives a logic judgment value of the on-off state of the hatch, and sends the judgment value to the hatch drive module signal amplifier, and then sends it to the hatch display for hatch state display after the drive module;

[0021] S6, the control system monitors whether the working voltage and current of the internal interface circuit, power circuit and drive circuit module of the control system are within the working range.

[0022] An aircraft cabin door control assembly, the cabin door control assembly comprises a plurality of cabin door position proximity sensor processing modules, a plurality of cargo door drive modules, a boarding bridge drive module and a generator load monitoring, APU fire warning circuit control module.

[0023] Compared with the prior art, the beneficial effects of the present application are as follows:

[0024] 1、The present application provides the collection, transmission, processing, position state indication and abnormal alarm of the aircraft cabin door position sensor signal by designing the aircraft cabin door signal control system and control assembly, and at the same time provides the BITE self-detection function of the aircraft cabin door control system, reduces the probability of operation error of the crew, and improves the safety during flight.

[0025] 2、According to the inductance value collected by the cabin door position proximity sensor collected by the microprocessor, the opening and closing state threshold value of the cabin door position is set; the microprocessor compares the collected inductance value with the opening and closing threshold value, and when the opening and closing state threshold value is exceeded, the microprocessor gives the cabin door opening and closing state logical judgment value, and sends the judgment value to the cabin door drive module signal amplification, and sends it to the cabin door display after the drive module to display the cabin door state.

[0026] 3、The control system monitors the working voltage and current of the internal interface circuit, power supply circuit and drive circuit module of the control system, and stops detection and gives an alarm when data overrun occurs; after the sensor data collection is completed, data processing is carried out, and the system alarms when the collected data exceeds the normal value. DETAILED DESCRIPTION

[0027] Figure 1 The functional diagram of the aircraft cabin door signal control system of the present application;

[0028] Figure 2 The frame diagram of the aircraft cabin door signal system of the present application;

[0029] Figure 3 The principle structure diagram of the eddy current proximity sensor signal collection of the present application;

[0030] Figure 4 The schematic diagram of the inductance collection structure circuit design of the present application;

[0031] Figure 5 The schematic diagram of the power supply interface circuit design of the present application;

[0032] Figure 6 The schematic diagram of the cabin door position sensor drive circuit of the present application. DETAILED DESCRIPTION

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] like Figures 1-6 As shown, an aircraft door control system includes a microprocessor module, an interface circuit module, a drive module, a door signal logic control module, and a self-detection module. The microprocessor unit includes an A / D conversion module and a data processing and logic judgment unit.

[0035] The interface circuit module includes several aircraft door position sensors and slide pre-position inductor sensor signals;

[0036] The drive module includes door drive, slide drive, and fire alarm drive;

[0037] The self-testing module includes a fault detector;

[0038] Furthermore, the microprocessor module, interface circuit module, drive module, door signal logic control module, and self-test module are electrically connected to each other.

[0039] The microprocessor unit includes an A / D conversion module and a data processing and logic judgment unit. It is responsible for transmitting the analog input signals collected by the door position sensors to the A / D conversion module, converting them into digital signals, and then outputting them to the microprocessor's data processing and logic judgment unit for data processing, calculation, and logical judgment. The results are then provided to the door drive for signal driving processing. Additionally, the microprocessor's data processing and logic judgment unit receives signals from the APU fire alarm monitoring module and the generator load monitoring module, monitoring the operation of the APU fire alarm and generator load. Finally, the microprocessor unit performs a self-test for the control components (BITE) function, issuing a controller fault warning message in case of any abnormality to prevent incorrect indications or malfunctions.

[0040] The interface circuitry includes the acquisition and processing of signals from nine aircraft door position sensors and one slide pre-position inductive sensor. The APU fire alarm and generator load monitoring signals are digital signals, and the microprocessor I / O ports are configured for reading. All nine door position sensors and the one slide pre-position sensor are eddy current proximity sensors.

[0041] The eddy current proximity sensor is also called non-contact travel switch, which uses the eddy current effect to convert displacement into the change of inductance, thereby performing non-electricity electrical measurement. The eddy current proximity sensor used on the aircraft door can detect whether there is an object close to the door within a distance of several millimeters to tens of millimeters, convert the position signal into inductance output, and thereby realize signal conversion and transmission.

[0042] The inductance measurement uses the principle of high-frequency oscillation of capacitor to collect inductance. Assuming that the inductance to be measured is L, and the output oscillation frequency is:

[0043]

[0044] From the above formula of oscillation frequency, the calculation formula of inductance can be derived as:

[0045]

[0046] The microprocessor is used to realize data acquisition and processing of the door sensor, directly collect inductance values of the sensor, and correspond the inductance values with the measurement distance, so that the sensor parameter dynamic configuration function can be realized, and the dynamic characteristic curve of the sensor can be monitored in real time, which greatly improves the measurement accuracy and realizes high-precision detection distance. The microprocessor unit controls each sensor signal independently, monitors the actual state of the door by measuring the actual inductance value of the sensor in real time, correctly sends the signal to the door display system, uses the high-speed analog-to-digital converter of the microprocessor to receive the signal data of the nine door sensors, sends the collected data to the microprocessor data processing and logic judgment unit for processing, and transmits the processed control signal to the drive module of the door and the slide.

[0047] The drive module includes door drive, slide drive and fire drive. The drive module receives the signal sent by the microprocessor and amplifies the signal, which is used for door state indication, controller and actuator work.

[0048] The self-detection (BITE) function mainly completes the self-detection of the internal interface circuit of the control system, the drive module and the internal processing module of the microprocessor. Once an abnormality occurs, a controller fault warning information is sent to prevent indication errors or misoperation.

[0049] The control system includes the following steps:

[0050] S1: In order to meet the system detection speed of the eddy current proximity sensor, a 12-bit A / D converter is selected, and the sampling clock frequency of the control system is 1 MHz;

[0051] S2: In order to meet the system running speed, STM32F4 series microprocessor is selected as the data processing and logic judgment unit, which meets the requirement of fast reading data after each AD sampling is completed.

[0052] S3: Interface circuit design, which mainly collects the inductance signal of the hatch position eddy current proximity sensor, and processes the signal through the collection of high frequency oscillation signal, provides the data operation for the microprocessor chip, and provides the inductance value corresponding to the actual position of the hatch. The inductance value and the threshold value of the hatch opening and closing inductance are judged, and finally the opening and closing state logic judgment value of the hatch is given.

[0053] S4: Power interface circuit design, in order to adapt to the power requirements of different chips and devices, and prevent mutual interference between each power supply, the power module adopts independent power supply mode, the system uses external 9-12V voltage power supply, according to the whole system demand, the power module is divided into digital power supply and analog power supply two independent parts. Digital power supply is used for microprocessor and A / D converter and other digital chip working voltage, voltage stabilizer selects 3.3V, 2.5V chip; Analog power supply uses 5V voltage stabilizer as digital power supply to provide working voltage.

[0054] S5: Drive circuit design, microprocessor chip directly controls solid state drive relay, solid state relay output end controls hatch actuator, controller and other functions, completes hatch opening and closing control, slide preposition control and hatch indication. The voltage of the hatch position sensor is DC 28V, the maximum output current is 5A, and the driving power supply is independent of the power module.

[0055] S6: The logic design of hatch signal logic control, according to the inductance value collected by the microprocessor and the hatch position proximity sensor, sets the hatch position opening and closing state threshold value; The microprocessor compares the collected inductance value with the opening and closing threshold value, and gives the hatch opening and closing state logic judgment value when the threshold value is exceeded, and sends the judgment value to the hatch drive module signal amplification, and sends it to the hatch display after the drive module to display the hatch state.

[0056] S7: Self detection (BITE) design, the control system monitors the working voltage and current of the internal interface circuit, power circuit and drive circuit module of the control system, and stops detection and gives an alarm when the data is out of limit; After the sensor data collection is completed, data processing is carried out, and the system gives an alarm when the collected data is out of normal value.

[0057] An aircraft cabin door control assembly, wherein the cabin door control assembly is the main body of the aircraft cabin door system, realizes various cabin door position sensor signal acquisition, signal processing, logic judgment and other functions, is composed of 9 cabin door position proximity sensor processing modules, 2 cargo door drive modules, 1 boarding bridge drive module and generator load monitoring, APU fire warning circuit control module, wherein the cabin door position proximity sensor processing module is the core unit of the controller design. The function of the sensor processing module is to correctly receive the actual position state instruction signal from each cabin sensor, process the instruction signal, logic judgment, amplification drive and other processes, and feedback to the cabin display system to give display and warning.

[0058] By designing the aircraft cabin door signal control system and control assembly, the real-time acquisition of the inductance parameters of the aircraft cabin door position sensor can be realized, and the inductance parameters are one-to-one corresponding to the actual position of the cabin door, so that the actual opening position in the opening and closing stroke of the cabin door can be accurately detected; a kind of aircraft cabin door signal logic control operation method is provided, according to the inductance value collected by the cabin door position proximity sensor collected by the microprocessor, the opening and closing state threshold of the cabin door position is set; the microprocessor compares the collected inductance value with the opening and closing threshold, and when the opening and closing state threshold is exceeded, the microprocessor gives the cabin door opening and closing state logic judgment value, and sends the judgment value to the cabin door drive module signal amplification, and sends it to the cabin door display after the drive module to display the cabin door state; and the BITE self-detection function of the aircraft cabin door control system is provided, which reduces the probability of operation error of the crew, and improves the safety during flight.

[0059] It should be noted that in this text, relationship terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment.

[0060] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to the embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An aircraft door control system, comprising a microprocessor module, an interface circuit module, a drive module, a door signal logic control module, and a self-detection module, characterized in that: The microprocessor module includes an A / D conversion module and a data processing and logic judgment unit; The interface circuit module includes several aircraft door position sensors and slide pre-position inductor sensor signals. The drive module includes a door drive, a slide drive, and a fire alarm drive. The self-testing module includes a fault detector; Furthermore, the microprocessor module, interface circuit module, drive module, door signal logic control module, and self-detection module are electrically connected to each other; the microprocessor unit independently controls each sensor signal. The interface circuit module also includes a power supply module, which is divided into a digital power supply and an analog power supply. The aircraft door position sensor and the slide pre-position inductance sensor are both eddy current proximity sensors. The inductance measurement uses the principle of high-frequency oscillation of capacitors to collect inductance. Includes the following steps: S1. Select a 12-bit A / D converter and control the system sampling clock frequency to 1MHz; S2. Utilize a microprocessor as a data processing and logic judgment unit to meet the requirements of rapid data reading after each AD sampling and complete the control system processing requirements. S3. Collect the inductance signal of the eddy current proximity sensor near the hatch, provide the inductance value corresponding to the actual position of the hatch, perform threshold judgment on the inductance value and the hatch opening / closing inductance, and finally give the hatch opening / closing state logic judgment value. S4. The solid-state drive relay is directly controlled by the microprocessor chip. The output of the solid-state relay controls the door actuator and controller to complete the door opening and closing control, slide pre-position control and door indication functions. S5. Based on the inductance value collected by the proximity sensor of the hatch position collected by the microprocessor, set the hatch position open and closed state threshold. The microprocessor compares the collected inductance value with the open and closed state threshold. If the inductance value exceeds the open and closed state threshold, the microprocessor gives the hatch open and closed state logic judgment value and sends the judgment value to the hatch drive module signal amplification. After passing through the drive module, the signal is sent to the hatch display for hatch status display. S6. The control system monitors whether the operating voltage and current of the internal interface circuit, power supply circuit, and drive circuit module are within the operating range.

2. The aircraft door control system according to claim 1, characterized in that: Both the analog and digital power supplies use a 5V voltage regulator to provide the operating voltage.

3. The aircraft door control system according to claim 2, characterized in that: The door position sensor uses a DC28V voltage, has a maximum output current of 5A, and is driven by a 28V independent power supply separate from the power module.

4. An aircraft door control assembly, controlled by an aircraft door control system as described in any one of claims 1-3, characterized in that: The door control assembly includes several door position proximity sensor processing modules, several cargo door drive modules, boarding ladder drive modules, and generator load monitoring and APU fire alarm warning circuit control modules.

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