CN210428133U

CN210428133U - Aircraft rear roof simulator

Info

Publication number: CN210428133U
Application number: CN201921329893.9U
Authority: CN
Inventors: 李权津; 钟宁伟; 刘怡
Original assignee: Xiamen Titan Avionics Technology Co Ltd
Current assignee: Xiamen Titan Avionics Technology Co Ltd
Priority date: 2019-08-16
Filing date: 2019-08-16
Publication date: 2020-04-28
Anticipated expiration: 2029-08-16

Abstract

The utility model relates to a roof simulator behind aircraft, the load simulator comprises a case, be provided with the back roof on the machine case, the below of back roof is provided with board in a poor light, the machine incasement is provided with power module and control panel, power module is used for supplying power for the control panel, be provided with the voltage reduction module on the control panel, the voltage reduction module is used for stepping down the voltage that power module provided, and supply power for board in a poor light and back roof, still be provided with microprocessor on the control panel, be provided with electric door and display screen on the back roof, the electric door is used for incoming signal to give microprocessor, microprocessor is used for handling the signal of input and exports the display screen and shows, microprocessor still communicates with data terminal through the USB interface. The utility model discloses a modular design for this product easy to maintain, installation convenient to use, this back roof simulator use experience and true aircraft and close, can provide a more true preceding roof learning environment for the flight student.

Description

Aircraft rear roof simulator

Technical Field

The utility model belongs to the technical field of the technique of flight emulation and specifically relates to a roof simulator behind aircraft.

Background

With the high-speed development of the current civil aviation industry, the maintenance personnel and flight personnel of the civil aircraft are seriously lacked, the corresponding civil aviation talent training industry develops vigorously, and the corresponding training equipment is produced. The rear roof, which is the most important component of an aircraft cockpit, appears in various forms at the relevant training authorities. With the discovery of science and technology and the improvement of teaching level, the simulation and reproduction technology of the rear top plate of the airplane cockpit is also greatly improved.

The technical specialties such as the knowledge ability required to be mastered by the training subjects of the civil aviation training institutions and the like are relatively strong, and the experience is accumulated by the actual operation within a certain time. For example, the maintenance personnel of the aircraft crew need to be skilled in mastering the functions and operation methods of each part, electric switch, button, indicator light and the like on the back top plate in the aircraft cockpit; for pilots to better understand the operation methods of electric doors on the back top plate and the significances represented by indicator lights, training organizations are required to provide real or near-real airplane cockpit back top plates for trainees to learn and operate by hands.

At present, most of the simulation equipment used by training institutions displays the picture of a rear top plate of a cockpit by using a computer display, and operates a switch, light and the like on the rear top plate by using simulation software and a mouse. The simulation mode cannot provide a real cockpit environment, cannot feel the operation feeling of each electric switch on the rear top plate, and cannot obtain a good learning effect.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a roof simulator behind aircraft solves the back roof simulator on the existing market and can only use mouse to operate, does not have three-dimensional sensation, and unable true touch influences the technical problem of learning effect.

The utility model provides a technical scheme that its technical problem adopted is:

the utility model provides an aircraft back roof simulator, includes quick-witted case, be provided with the back roof on the quick-witted case, the below of back roof is provided with board in a poor light, the quick-witted incasement is provided with power module and control panel, power module is used for supplying power for the control panel, be provided with the step-down module on the control panel, the step-down module is used for stepping down the voltage that power module provided to supply power for board in a poor light and back roof, still be provided with microprocessor on the control panel, be provided with electric door and display screen on the back roof, the electric door is used for incoming signal to give microprocessor, and microprocessor is used for handling the signal of input and exports to the display screen and shows, microprocessor still communicates with data terminal through the USB interface.

Further, the rear top plate comprises an ELT emergency positioning transmitter panel, a front edge device indicating panel, a PSEU proximity switch electronic component lamp, an inertia reference display component, a mode selection component, a service internal call switch, a lamp light dark and bright control switch, an audio selection control panel, an engine panel, an oxygen panel, an undercarriage position indicating lamp, a flight recorder control panel, a Mach airspeed warning test switch and a stall warning test switch.

Further, the ELT emergency positioning transmitter panel comprises an ELT emission indicator lamp and an ELT control electric gate, wherein the ELT control electric gate is used for starting an emergency emission function of the ELT under an emergency condition, and the ELT emission indicator lamp is lightened when the ELT control electric gate is arranged at an ON position.

Further, leading edge device indicator panel includes status indicator lamp and test light, the status indicator lamp includes leading edge flap conversion and stretches out the lamp to and slat conversion, stretch out and stretch out the lamp entirely, the test light is used for testing the fault condition of status indicator lamp, leading edge flap conversion and stretch out the lamp and slat conversion, stretch out and stretch out the lamp entirely and be used for lighting according to the action of leading edge flap and slat.

Further, the inertial reference display assembly comprises a data display window, a display selection electric door and a keyboard, wherein the data display window comprises a left part and a right part and is used for displaying inertial reference system data selected by the selection electric door, the keyboard is used for inputting data, the display selection electric door is used for determining the data type displayed by the data display window, the current position input by the keyboard or the display of magnetic heading override selection, and the last digit of each data display window is a decimal digit.

Further, the mode selection assembly comprises a global positioning system GPS indicator light, a left inertial reference system mode selection switch and a right inertial reference system mode selection switch, the global positioning system GPS indicator light is used for indicating whether the global positioning system sensor assembly fails, the left inertial reference system mode selection switch and the right inertial reference system mode selection switch are used for starting a calibration cycle, and the mode selection assembly further comprises a calibration indicator light, a fault light, a direct current connection indicator light and a direct current failure indicator light which are respectively used for indicating corresponding information.

Further, the audio selection control panel includes a transmitter selection switch for indicating whether the switch is turned on, a receiver switch for pressing a signal for receiving a corresponding communication system or navigation receiver, a receiver switch for rotating for adjusting a volume, and a filter switch for receiving an audio signal.

Further, the engine panel includes backstepping pilot lamp, engine control pilot lamp, engine electronic control switch, the backstepping pilot lamp is used for instructing whether backstepping control valve is in the instruction state, the engine control pilot lamp is used for instructing engine system trouble, the different colours of engine electronic control switch are used for instructing the different states of engine electronic controller respectively.

Further, the oxygen panel includes flight unit oxygen manometer, passenger oxygen electric door, passenger oxygen switch on lamp, flight unit oxygen manometer is used for instructing the pressure of flight unit oxygen cylinder, the passenger oxygen electric door is used for controlling passenger oxygen's supply, passenger oxygen switch on lamp is lighted and is used for showing that passenger oxygen system is working and the face guard has come off.

Further, the data display window adopts an OLED display screen.

The utility model has the advantages that: the utility model discloses simple structure is compact, reasonable in design, and the cost is lower, and the fidelity is high, and simulation effect is showing, has good experience effect, and the back roof simulator of modular design makes this product easy to maintain simultaneously, installs convenient to use, and this back roof simulator uses experience and true aircraft and is close, can provide a more real preceding roof learning environment for the flight student.

Drawings

The embodiments of the present invention will be further described with reference to the accompanying drawings:

fig. 1 is a schematic view of a rear top plate according to a preferred embodiment of the present invention;

fig. 2 is a block diagram of the working principle of the preferred embodiment of the present invention.

Detailed Description

In order to make the technical solution of the present invention better understood, the technical solution of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

Referring to fig. 1 and 2, the aircraft back roof simulator of the embodiment includes a chassis, a back roof is disposed on the chassis, a backlight panel is disposed below the back roof, a power module and a control panel are disposed in the chassis, the power module is used for supplying power to the control panel, a voltage reduction module is disposed on the control panel, the power module provides a 5V 8A dc power supply for the control panel, the voltage reduction module reduces a 5V voltage to 3.3V and supplies power to the backlight panel and the back roof, a microprocessor is further disposed on the control panel, an electric gate and a display screen are disposed on the back roof, the electric gate is used for inputting signals to the microprocessor, the microprocessor is used for processing the inputted signals and outputting the processed signals to the display screen for displaying, the control panel is connected with the back roof through data transmission, receives the inputted signals of each part of the back roof and provides the same control logic as that of, the control board and the data terminal are connected through a USB2.0 interface and can communicate with software such as PMDG, iFly, ProSim, Project Magenta and the like, so that when parts on the back top plate are operated, the same feedback effect as that of a real airplane can be obtained. The backlight plate is used for providing a backlight effect with adjustable luminosity.

The rear roof panel includes an ELT emergency positioning transmitter panel 10, a leading edge device indicator panel 20, a PSEU proximity switch electronic assembly light 30, an inertial reference display assembly 40, a mode selection assembly 50, a service interphone switch light 60, a light dim-light control light 70, an audio selection control panel 80, an engine panel 90, an oxygen panel 100, a landing gear position indicator light 110, a flight recorder control panel 120, a mach airspeed warning test light 130, a stall warning test light 140.

The ELT emergency positioning transmitter panel 10 comprises an ELT emission indicator lamp 11 and an ELT control electric gate 12, wherein the ELT control electric gate 12 is protected by a red protective cover in a preset position (ARM), when the emergency emission function of the ELT needs to be started under the emergency condition, the protective cover is opened, the ELT control electric gate 12 is placed at an ON position, and the ELT emission indicator lamp 11 is lightened to indicate that the ELT emergency positioning function is started.

The leading edge device indication panel 20 comprises a status indicator lamp 21 and a test electric door 22, the status indicator lamp 21 comprises a leading edge flap switching and extending lamp and a leading edge slat switching, extending and fully extending lamp, the test electric door 22 is used for testing and checking whether the lamps on the leading edge device indication panel 20 can be normally lighted, and when the test electric door 22 is pressed, the lamps on the panel are lighted. When the leading edge flap is in the upper position, the conversion lamp and the extension lamp are both extinguished, the conversion lamp is lightened when the leading edge flap moves from the upper position to the extension position, and when the leading edge flap reaches the extension position, the extension lamp is lightened and the conversion lamp is extinguished. When the leading edge slat is in a manual position, all the lamps are turned off, when the leading edge slat moves, the conversion lamp is turned on, when the leading edge slat reaches the extension position, the extension lamp is turned on, when the leading edge slat reaches the full extension position, the full extension lamp is turned on, and the extension lamp and the conversion lamp are turned off.

The PSEU proximity gate electronics package light 30 is used to indicate the status of the proximity gate electronics package and to illuminate the PSEU light after the aircraft lands when a fault is detected in the proximity gate electronics package.

The inertial reference display assembly 40 includes a data display window 41, a display selection electric gate 42 and a keyboard 43, the data display window 41 is divided into a left part and a right part and is used for displaying inertial reference system data selected by the selection electric gate, the keyboard 43 is used for inputting data, the display selection electric gate 42 determines the type of data displayed, the current position input by the keyboard 43 or the display of magnetic heading override selection, the last digit of each window is decimal (one tenth), and the display selection electric gate 42 selects the type of data displayed in the data display window 41: TEST (TEST), track/ground speed (TK/GS), current position (PPOS), WIND (WIND), heading/status (HDG/STS). A Brightness (BRT) control knob at the upper part of the selection switch can adjust the display brightness of the data display window 41, and a system display (SYSDSPL) selection switch is used for selecting a left/right inertia reference system for data display.

The data display window 41 adopts an OLED display screen, has a higher resolution, is different from the nixie tube display on the market, and can display more and more accurate symbols. The display device has the advantages of multistage brightness adjustment, adoption of the SPI high-speed interface, capability of well finishing display of various characters and the like, high page refreshing response speed and no pause feeling.

The mode selection assembly 50 includes a global positioning system GPS indicator light 51, left and right inertial reference system mode selection gates 52, a calibration ALIGN indicator light, a FAULT light, a DC ON DC indicator light, and a DC FAIL indicator light.

The global positioning system GPS indicator light 51 is on (amber) indicating: indicating failure of both gps sensor assemblies; when any system signal board is reproduced, the lamp is on, and the single global positioning system sensor assembly is indicated to be invalid; if the single global positioning system sensor fails, the indicating lamp is turned off when the system is reset again.

The left-right inertia reference system mode selection switch 52 is in the OFF position: loss of calibration, system power outage after 30 seconds of off cycle; after calibrating ALIGN bit: turning the electric gate from the off position to the calibration position, and starting a calibration cycle; the electric switch is switched from the navigation position to the calibration position, the calibration is automatically updated, and the ground speed error is corrected to zero; in the navigation NAV bit: after completing the calibration cycle and inputting the current position, the system enters a navigation mode; in the navigation mode, all the information of the inertial reference system can be used for normal operation of an aircraft system; at pose ATT position: only pose and heading information is provided: before the calibration indicator light is turned off, the posture information is invalid (the posture flag is visible); after the calibration indicator light is turned off, manually inputting the actual magnetic navigation forward, and making the course information invalid (the course flag is visible); before the ground calibrates the inertial reference system, the position and ground speed information is unavailable; before the calibration or navigation bit is reselected, the select gate must be placed in the off position.

Calibration ALIGN indicator light on (white) indicates: a is stable and bright: the corresponding inertial reference system works in a calibration mode, an initial attitude mode or a shutdown cycle mode; b, flashing: calibration cannot be done because the inertial reference system detects the following: the position of the last time is obviously different from the input position or the input current position is not reasonable and the current position is not input. Calibration ALIGN indicator light off indicates: the inertial reference system is not in a calibration mode; the mode selection switch is in a navigation position, calibration is completed, and all the inertial reference system information is available; the mode selection switch is in the attitude position, the attitude information is available, and the initial magnetic heading information is available after being input.

FAULT indication FAULT light on (amber) indicates: system faults are detected that affect the attitude and/or navigation mode of the corresponding inertial reference system.

The direct current ON indication ON DC lamp is bright (amber) indicating: the corresponding inertial reference system is operating using the dc power supply of the converted thermos bus bar (ac power supply is not normal); if on the ground, the ground of the front wheel cabin calls a horn to sound, and the warning of battery discharge is provided; during calibration self-test, the instantaneous light is normal.

The DC FAIL indication DC FAIL light on (amber) indicates: the corresponding inertia reference system DC power supply is abnormal; if other lamps are turned off, the inertial reference system works normally by using an alternating current power supply.

The service intercom gate 60 is used to switch the service intercom function.

The lamp light dimming control switch 70 is used for controlling dimming of light on the rear ceiling plate, and when the switch is set to an OFF position, the light is not lit; when the switch is arranged at DIM position, the light is dark and bright; when the electric gate is at BRIGHT position, the light is BRIGHT.

The audio selection control panel 80 comprises a transmitter selection switch 81, a receiver switch 82 and a filter switch 83, and when the transmitter selection switch 81 is lighted, the corresponding switch is turned on, and the pressing of the corresponding switch will: the corresponding communication system is selected to transmit, only one electric gate is selected at a time, the other electric gate is pressed, namely, the original selected electric gate is released, and the user can listen to the system through the selected electric gate whether the corresponding receiving electric gate is connected or not. The receiver switch 82 presses the corresponding switch to switch on the switch, the volume can be adjusted by rotating the switch, and the pressing of the switch can: allowing reception of signals of the respective communication system or navigation receiver; a plurality of electric switches can be selected, pressed again: the corresponding system or receiver deselects. The filter gate 83 is a three-bit selection gate, speech (V): navigation device (NAV) and ADF (automatic direction finder) voice audio signals are received. Dibit (B): receive navigation device and ADF (automatic orientation instrument) speech and band audio signals. Band (R): band (code) audio signals of a navigation device and an ADF (automatic direction finder) station call sign are received.

The engine panel 90 comprises a reverse-thrust indicator light 91, an engine control indicator light 92 and an engine electronic control switch 93, wherein the reverse-thrust indicator light 91 is bright (amber) to show that: the isolation valve or the reverse thrust control valve is not at the position of the instruction; one or more thrust sleeves are not in a commanded state; the automatic recovery circuit has been activated; a synchronization shaft lock circuit fault is detected. The engine control indicator 92 is on (amber) to indicate: the engine control system is not enabled due to system failure. The engine control indicator 92 is on with the engine on the ground and the aircraft at a pre-takeoff speed of less than 80 knots, or about 30 seconds after ground contact. The engine electronic control switch 93 is bright (white) to indicate: indicating to select a normal control mode; according to the measured environmental conditions and the air entraining requirements, an engine electronic controller calculates the thrust level of the engine; not shown ON, the engine electronic control assembly has been manually selected to be in a standby mode. The engine electronic control gate 93 is in the standby position, light (amber) indicating: indicating that the electronic control of the engine has been automatically changed to a standby mode of operation or has been manually selected; the engine electronic control provides rated or greater thrust.

Oxygen panel 100 includes flight crew oxygen pressure gauge 101, passenger oxygen electric door 102, passenger oxygen switch on lamp 103, and flight crew oxygen pressure gauge 101 is used for instructing the pressure of flight crew oxygen cylinder, and passenger oxygen electric door 102 is used for controlling the supply of passenger oxygen, at NORMAL position (NORMAL): when the cabin height climbs to 14000 feet, the passenger oxygen mask falls off and the passenger oxygen system automatically works, and in an open position (ON): if the automatic function fails, the system is enabled and the mask is removed. The passenger oxygen on light 103 is on (amber) indicating: the passenger oxygen system is working and the mask has fallen off.

The landing gear position indicator lights 110 are three and indicate the state of the nose landing gear, the left landing gear and the right landing gear, respectively, and when the corresponding landing gear is down and locked, the corresponding indicator light (green) is turned on, otherwise the lights are not turned on.

The rear top plate simulator with the modular design ensures that the product is easy to maintain, convenient to install and use, compact in structure and small in occupied space. The material is close to the profile on a real airplane, so that the use experience of the back top plate simulator is similar to that of the real airplane, and a real back top plate learning environment can be provided for flight trainees. In addition, the disassembly and assembly modes of all modules or the whole rear top plate simulator are consistent with those of a real aircraft rear top plate, and a real aircraft rear top plate maintenance environment can be provided for aircraft maintenance trainees.

In summary, the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art; the technical solutions described in the foregoing embodiments can be modified or equivalent replaced without losing the technical features, and such modifications or replacements do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft rear roof simulator, characterized in that: the intelligent control cabinet is characterized by comprising a cabinet, a rear top plate is arranged on the cabinet, a backlight plate is arranged below the rear top plate, a power module and a control plate are arranged in the cabinet, the power module is used for supplying power to the control plate, a voltage reduction module is arranged on the control plate and used for reducing the voltage provided by the power module and supplying power to the backlight plate and the rear top plate, a microprocessor is further arranged on the control plate, an electric door and a display screen are arranged on the rear top plate, the electric door is used for inputting signals to the microprocessor, the microprocessor is used for processing the input signals and outputting the input signals to the display screen for displaying, and the microprocessor is further communicated with a data terminal through a USB interface.

2. An aircraft rear roof simulator according to claim 1, in which: the rear top plate comprises an ELT emergency positioning transmitter panel, a front edge device indicating panel, a PSEU proximity switch electronic component lamp, an inertia reference display component, a mode selection component, a service internal call switch, a lamp light dim-light control switch, an audio selection control panel, an engine panel, an oxygen panel, an undercarriage position indicating lamp, a flight recorder control panel, a Mach airspeed warning test switch and a stall warning test switch.

3. An aircraft rear roof simulator according to claim 2, wherein: the panel of the ELT emergency positioning transmitter comprises an ELT emission indicator lamp and an ELT control electric gate, wherein the ELT control electric gate is used for starting an emergency emission function of the ELT under an emergency condition, and the ELT emission indicator lamp is lightened when the ELT control electric gate is arranged at an ON position.

4. An aircraft rear roof simulator according to claim 2, wherein: the leading edge device indicating panel comprises a state indicating lamp and a testing electric door, the state indicating lamp comprises a leading edge flap switching and extending lamp and a leading edge slat switching, extending and fully extending lamp, the testing electric door is used for testing the fault condition of the state indicating lamp, and the leading edge flap switching and extending lamp and the leading edge slat switching, extending and fully extending lamp are used for lighting according to the actions of the leading edge flap and the slat.

5. An aircraft rear roof simulator according to claim 2, wherein: the inertial reference display assembly comprises a data display window, a display selection electric door and a keyboard, wherein the data display window comprises a left part and a right part and is used for displaying inertial reference system data selected by the selection electric door, the keyboard is used for inputting data, the display selection electric door is used for determining the data type displayed by the data display window, the current position input by the keyboard or the display of magnetic heading override selection, and the last digit of each data display window is a decimal digit.

6. An aircraft rear roof simulator according to claim 2, wherein: the mode selection assembly comprises a Global Positioning System (GPS) indicating lamp and a left and right inertia reference system mode selection switch, the GPS indicating lamp is used for indicating whether the GPS sensor assembly fails, the left and right inertia reference system mode selection switches are used for starting a calibration cycle, and the mode selection assembly further comprises a calibration indicating lamp, a fault lamp, a direct current connection indicating lamp and a direct current failure indicating lamp which are respectively used for indicating corresponding information.

7. An aircraft rear roof simulator according to claim 2, wherein: the audio selection control panel comprises a transmitter selection switch, a receiver switch and a filter switch, wherein the transmitter selection switch is used for indicating whether the switch is switched on or not, the receiver switch is pressed to receive signals of a corresponding communication system or a navigation receiver, the receiver switch is rotated to adjust the volume, and the filter switch is used for receiving audio signals.

8. An aircraft rear roof simulator according to claim 2, wherein: the engine panel includes reverse-push pilot lamp, engine control pilot lamp, engine electronic control electric door, the reverse-push pilot lamp is used for instructing whether reverse-push control valve is in the instruction state, the engine control pilot lamp is used for instructing engine system trouble, the different colours of engine electronic control electric door are used for instructing the different states of engine electronic controller respectively.

9. An aircraft rear roof simulator according to claim 2, wherein: the oxygen panel includes flight crew oxygen manometer, passenger oxygen electric door, passenger oxygen switch on lamp, flight crew oxygen manometer is used for instructing the pressure of flight crew oxygen cylinder, passenger oxygen electric door is used for controlling passenger oxygen's supply, passenger oxygen switch on lamp lights and is used for showing that passenger oxygen system is working and the face guard has come off.

10. An aircraft rear roof simulator according to claim 5, wherein: the data display window adopts an OLED display screen.