CN210639792U - Aircraft front roof simulator - Google Patents

Abstract

The utility model relates to a roof simulator before aircraft, the load simulator comprises a case, be provided with preceding roof on the machine case, the below of preceding roof is provided with the 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 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 preceding roof, still be provided with microprocessor on the control panel, microprocessor is used for communicating with preceding roof and data terminal. The utility model discloses simple structure is compact, reasonable in design, and the cost is lower, and the fidelity is high, and the simulation effect is showing, has good experience effect, and the preceding roof simulator of modular design makes this product easy to maintain simultaneously, installs convenient to use, and this preceding roof simulator uses experience and true aircraft and is close, can provide a more true preceding roof learning environment for the flight student.

Description

Aircraft front 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 before 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 front roof, 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 front top plate of the cockpit of the airplane 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 front top plate in the aircraft cockpit; for pilots to better understand the operation methods of electric doors on the front top plate and the significances represented by indicator lights, training organizations are required to provide real or near-real airplane cockpit front top plates for trainees to learn and operate by hands.

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

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aircraft nose board simulator solves the nose board 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 front roof simulator, includes quick-witted case, be provided with the front roof on the quick-witted case, the below of front roof is provided with the 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 voltage reduction module on the control panel, the voltage reduction module is used for stepping down the voltage that power module provided to supply power for board in a poor light and front roof, still be provided with microprocessor on the control panel, microprocessor is used for communicating with front roof and data terminal.

Further, the front top plate comprises a middle miscellaneous panel, a flight control panel, a power supply control panel, an instrument selection panel, a standby power supply control panel, a fuel control panel, a generator control panel, a heating control panel, an anti-icing control panel, a temperature control panel, a hydraulic control panel, an air conditioner control panel, a cabin door display panel, a voice test panel, a height display panel and a pressurization control panel are respectively arranged on two sides of the middle miscellaneous panel, and a light control panel, an auxiliary power starting panel and an engine control panel are sequentially arranged at the bottom of the middle miscellaneous panel from left to right.

Further, flight control panel includes flight control power gate, flight control low pressure lamp, flight spoiler power gate, driftage damper power gate and driftage damper lamp, the flight control power gate is used for controlling reserve hydraulic pump and opens reserve rudder and shuts OFF the valve, flight control low pressure lamp is used for lighting when system hydraulic pressure is low, the flight spoiler power gate is used for control system pressure supply flight spoiler system, the driftage damper power gate is used for when flight relevant system is unsatisfied, and the driftage damping is thrown OFF, realizes the automatic OFF position that rebounds back through steering wheel and permanent magnet cooperation, the driftage damper lamp is used for lighting when the automatic OFF position that rebounds back of driftage damper power gate.

Further, the power control panel comprises a power parameter display screen, a battery discharge indicator lamp, a power conversion component lamp, an electric lamp, a maintenance electric door, a direct current selection electric door, a battery electric door, an alternating current selection electric door, a cabin power supply and an entertainment system power switch electric door, wherein the power parameter display screen adopts an OLED display screen for displaying direct current voltage parameters, alternating current voltage and frequency parameters and fault codes, the battery discharge indicator lamp is used for indicating the discharge state of the battery, the power conversion component lamp is used for being lightened when the system detects the fault of the power conversion component, the electric lamp is used for being lightened when the system detects the fault of the electric system, the maintenance electric door is used for maintaining the power system, the direct current selection electric door is used for selecting a display source of the direct current parameters on the power parameter display screen, and the battery electric door is used for switching on and off the battery, the alternating current selection electric door is used for selecting a display source of alternating current parameters on the power supply parameter display screen, and the cabin power supply and entertainment system power supply switch electric door is used for controlling a power supply in a cabin and a power supply of a cabin entertainment system.

Further, the fuel control panel includes that the engine valve closes pilot lamp, wing spar valve pilot lamp, fuel and strains bypass pilot lamp, handing over valve pilot lamp and fuel temperature indicator, the engine valve closes the state that the pilot lamp is used for instructing the interior fuel of engine and shuts off the valve, wing spar valve pilot lamp is used for instructing the state of engine wing spar valve, the bypass pilot lamp is strained to fuel is used for instructing the state that the engine fuel was strained, handing over the position state that the valve pilot lamp is used for instructing the fuel system handing over the valve, the fuel temperature indicator is controlled by the control board for according to user-defined temperature value of instructing of user.

Further, stand-by power supply control panel includes stand-by power supply disconnection lamp, engine drive pilot lamp, engine drive disconnection electric door and stand-by power supply electric door, stand-by power supply disconnection lamp is used for lighting when stand-by power supply electric door is in the OFF position, engine drive pilot lamp is used for lighting when engine drive disconnection electric door is opened.

Further, the intermediate miscellaneous panel comprises an equipment cooling electric door, an equipment cooling indicator lamp, an emergency exit lamp switch, an emergency exit lamp non-preposition indicator lamp, a smoking prohibition electric door, a fastened safety belt electric door, a crew call electric door, a call ground electric door and a call indicator lamp, wherein the equipment cooling electric door is used for opening the equipment cooling system, the equipment cooling indicator lamp is lightened when the equipment cooling system fails, the emergency exit lamp non-preposition indicator lamp is used for lightening when the emergency exit lamp switch is arranged at an OFF position, the smoking prohibition electric door and the fastened safety belt electric door are used for controlling the smoking prohibition lamp and the fastened safety belt lamp of the passenger cabin, the crew call electric door and the call ground electric door are electric doors used when calling outside personnel, and the call indicator lamp is used for lightening when the outside personnel call the cab.

Further, engine control panel selects the electric door and engine start-up electric door including igniteing, the IGN L gear of ignition selection electric door selects left point firearm for two engines, and IGN R gear selects right point firearm for two engines, and BOTH selects two point firers for two engines, engine start-up electric door is controlled by the control panel, realizes the automatic OFF position that rebounds through steering wheel and arm cooperation.

Further, the control panel that heats includes that the windscreen warms up lamp, windscreen heats up the lamp, the windscreen heats the electric door, the windscreen heats test electric door, pitot tube heats up lamp and pitot tube and heats the control electric door, the windscreen heats the electric door and is used for controlling the heating of two front windshields and two side windshields in the cockpit, the windscreen warms up the lamp and is used for instructing the state that the windscreen heated up, the windscreen is overheated the state that whether the lamp is used for instructing the windscreen to heat up, the windscreen heats test electric door and is used for testing the windscreen and heats the electric door, the pitot tube heats the control electric door and is used for controlling the heating of pitot tube, the pitot tube is heated up the lamp and is used for instructing the state that the pitot tube heated.

Further, anti-icing control panel includes that wing anti-icing valve opens the lamp, engine fairing anti-icing valve opens lamp, fairing anti-icing lamp, wing anti-icing control electric door, engine anti-icing control electric door, wing anti-icing control electric door is used for controlling the switch of controlling two wing anti-icing valves, wing anti-icing valve opens the on off state that the lamp is used for instructing corresponding wing anti-icing valve, engine anti-icing control electric door is used for controlling the switch of engine fairing anti-icing valve, engine fairing anti-icing valve opens the on off state that the lamp is used for instructing corresponding fairing anti-icing valve, fairing anti-icing lamp is used for instructing the operating condition of corresponding fairing anti-icing valve.

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 the simulation effect is showing, has good experience effect, and the preceding roof simulator of modular design makes this product easy to maintain simultaneously, installs convenient to use, and this preceding roof simulator uses experience and true aircraft and is close, can provide a more true 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 block diagram of the working principle of the preferred embodiment of the present invention;

fig. 2 is a schematic view of a front top plate according to a preferred embodiment of the present invention;

FIG. 3 is a schematic view of a flight control panel according to a preferred embodiment of the present invention;

fig. 4 is a schematic diagram of a power control panel according to a preferred embodiment of the present invention;

FIG. 5 is a schematic view of a fuel control panel according to a preferred embodiment of the present invention;

fig. 6 is a schematic diagram of a standby power control panel according to a preferred embodiment of the present invention;

FIG. 7 is a schematic view of a middle miscellaneous panel in accordance with a preferred embodiment of the present invention;

FIG. 8 is a schematic view of an engine control panel according to a preferred embodiment of the present invention;

fig. 9 is a schematic view of a heating control panel according to a preferred embodiment of the present invention;

FIG. 10 is a schematic view of an anti-icing control panel according to a preferred embodiment of the present invention;

FIG. 11 is a schematic view of a voice test panel according to a preferred embodiment of the present invention;

fig. 12 is a schematic view of a temperature control panel according to a 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, the aircraft front roof simulator of this embodiment, which comprises a case, is provided with front roof 1 on the machine case, and front roof 1's below is provided with the board in a poor light, and the machine incasement is provided with power module and control panel, and power module is used for supplying power for the control panel, is provided with the voltage reduction module on the control panel, and the voltage reduction module is used for stepping down the voltage that power module provided to supply power for board in a poor light and front roof 1, still is provided with microprocessor on the control panel, and microprocessor is used for communicating with front roof 1 and data terminal. The power module provides a 5V 8A's DC power supply for the control panel, the step-down module is 3.3V with 5V voltage step-down, and supply power for backlight and preceding roof 1, the control panel is connected through data transmission with preceding roof 1, receive the input signal of each part of preceding roof 1, and provide the same control logic with on the real aircraft, control panel and data terminal realize connecting through a USB2.0 interface, can communicate with software such as PMDG, iFly, ProSim, Project Magenta, make when the part on the roof before the operation, can obtain the same feedback effect with on the real aircraft. The backlight plate is used for providing a backlight effect with adjustable luminosity.

Referring to fig. 2, the front top board 1 includes a middle miscellaneous item panel 10, a flight control panel 20, a power control panel 30, an instrument selection panel 40, a standby power control panel 50, a fuel control panel 60, a generator control panel 70, a warming control panel 80, an anti-icing control panel 90, a temperature control panel 100, a hydraulic control panel 110, an air conditioner control panel 120, a hatch display panel 130, a voice test panel 140, a height display panel 150, and a pressurization control panel 160 are respectively disposed on two sides of the middle miscellaneous item panel 10, and a light control panel 170, an auxiliary power start panel 180, and an engine control panel 190 are sequentially disposed at the bottom of the middle miscellaneous item panel 10 from left to right.

Referring to fig. 3, the flight control panel 20 includes a flight control electric gate 21, a flight control low-voltage lamp 22, a flight spoiler electric gate 23, a yaw damper electric gate 24, and a yaw damper lamp 25, the flight control electric gate 21 is used to control the backup hydraulic pump and open the backup rudder shutoff gate to pressurize the backup rudder power control assembly; the flight control low pressure lamp 22 is used for lighting when the system hydraulic pressure is low, the flight spoiler electric door 23 is covered by the protective cover at the normal working position and used for controlling the system pressure to supply the flight spoiler system, and the corresponding flight control low pressure lamp 22 is lighted when the system hydraulic pressure is low in the flight control A, B. The yaw damper electric door 24 is used for enabling yaw damping to be disengaged when a flight related system is not met, automatic rebounding of an OFF position is achieved through cooperation of the steering engine and the permanent magnet, and the yaw damper lamp 25 is used for being turned on when the yaw damper electric door 24 automatically rebounds of the OFF position. Normally, after the yaw damper gate 24 is set to the OFF position, the yaw damper lamp 25 is turned OFF, and when the aircraft phase relation system condition is not satisfied (for example, the inertial navigation system is calibrated), the yaw damper is turned OFF, and then the yaw damper gate 24 will automatically bounce back to the OFF position, and the yaw damper lamp 25 is turned on. To the realization of this function, the true aircraft uses is that the higher solenoid of precision realizes, gives a current signal when the condition satisfies, and solenoid work produces electromagnetic attraction, with the electric door actuation to the OFF position, in view of this solenoid is with high costs, the utility model discloses a steering wheel and permanent magnet realize this function: when the conditions are met, a current signal is given to enable the steering engine to move, the steering engine drives the permanent magnet to move to the position near the yaw damping electric door 24, so that the electric door is attracted to the OFF position, and then the steering engine resets to prepare for the next movement.

Referring to fig. 4, the power control panel 30 includes a power parameter display screen 31, a battery discharge indicator lamp 32, a power conversion component lamp 33, an electric lamp 34, a maintenance electric door 35, a dc selection electric door 36, a battery electric door 37, an ac selection electric door 38, a cabin power and entertainment system power switch electric door 39, the power parameter display screen 31 adopts an OLED display screen for displaying parameters such as current and voltage parameters of dc, current and voltage and frequency parameters of ac, and a fault code, the battery discharge indicator lamp 32 is used for indicating a discharge state of the battery, when the system detects that the battery is discharging, a signal is given to light the battery discharge indicator lamp 32, the power conversion component lamp 33 is used for lighting when the system detects a power conversion component fault, the electric lamp 34 is used for lighting when the system detects an electrical system fault, the maintenance electric door 35 is used for maintaining the power system, the power parameter display screen 31 can be tested by pressing the maintenance switch 35, fault codes recorded in the system can be read out, the fault codes are displayed on the power parameter display screen 31, and the displayed fault codes can be eliminated by pressing the maintenance switch 35 for a long time. The dc power selection switch 36 is used for selecting a display source of the dc power parameter on the power parameter display screen 31, and includes: the test position, the stand-by power supply, the storage battery busbar, the storage battery, the auxiliary storage battery, the 1# power supply conversion assembly, the 2# power supply conversion assembly and the 3# power supply conversion assembly are selected to be in corresponding positions, and the direct current parameters of the system can be displayed in corresponding positions of the power supply parameter display screen 31. The battery electric gate 37 is used for switching on and off the battery, and the alternating current selection electric gate 38 is used for selecting a display source of alternating current parameters on the power supply parameter display screen 31, and the power supply parameter display screen 31 comprises the following components: the standby power supply, the ground power supply, the 1# generator, the APU (auxiliary power unit) generator, the 2# generator, the static current transformer and the test bit are selected to corresponding positions, so that the alternating current parameters of the system can be displayed at the corresponding positions of the power parameter display screen 31. The cabin power and entertainment system power switch electric door 39 is used to control the power in the cabin and the power of the cabin entertainment system. When the electric gate is set to ON, the corresponding system is powered ON, and when the electric gate is set to OFF position, the corresponding system is powered OFF.

Referring to fig. 5, the fuel control panel 60 includes an engine valve shut off indicator light 61, a spar valve indicator light 62, a fuel filter bypass indicator light 63, a transfer valve indicator light 64, and a fuel temperature indicator gauge 65, the engine valve shut off indicator light 61 is used to indicate the status of the fuel shutoff valve in the engine, when the engine is shut down, the engine valve shut-off indicator lamp 61 is turned on, when the engine is started, during the valve switching process, the engine valve shut-off indicator lamp 61 is turned on, when the engine is started and the valve is opened, the engine valve closing indicator lamp 61 is turned off, the spar valve indicator lamp 62 is used for indicating the state of the engine spar valve, the lighting condition is the same as that of the engine valve closing indicator lamp 61, the fuel filter bypass indicator lamp 63 is used for indicating the state of the fuel filter of the engine, when the fuel filter is bypassed, a voltage signal is given to enable the fuel filter bypass indicator lamp 6 to be lightened. The delivery valve indicator lamp 64 is used for indicating the position state of a delivery valve of the fuel system, when the fuel delivery valve is closed, the delivery valve indicator lamp 64 is off, when the delivery valve moves (moves from a closed position to an open position or moves from the open position to the closed position), the delivery valve indicator lamp 64 is on, and when the delivery valve is in the open position, the delivery valve indicator lamp 64 is on. The fuel temperature indicator 65 is controlled by the control board, the control board gives an electric signal to drive the steering engine to move, the steering engine drives the pointer to move to an indication of a temperature value, and the value can be customized by software. The lighting logic of the indicator light is consistent with that of a real airplane, and the corresponding state can be converted according to the starting process of the engine in the simulation.

Referring to fig. 6, the backup power control panel 50 includes a backup power cut-OFF lamp 51, an engine driving indicator lamp 52, an engine driving cut-OFF switch 53, and a backup power switch 54, the backup power switch 54 is normally protected by a black protective cover, the backup power switch 54 is a three-position switch, when the switch is placed in the OFF position, the backup power is cut OFF, and the backup power cut-OFF lamp 51 is turned on; when the electric door is placed at BAT position, the standby power supply is powered by the battery. The engine-driven indicator lamp 52 is lit when the backup power switch 54 is in the OFF position, and is lit when the engine-driven disconnection switch 53 is opened, and is normally covered with a red protective cover to protect against accidental actuation, and the engine-driven generator is disconnected from the engine and the engine-driven indicator lamp 52 is lit when the engine-driven disconnection switch 53 is opened.

Referring to fig. 7, the intermediate miscellaneous panel 10 includes an equipment cooling electric door 11, an equipment cooling indicator lamp 12, an emergency exit lamp switch 13, an emergency exit lamp non-preset indicator lamp 14, a smoking prohibition electric door 15, a seat belt electric door 16, a crew call electric door 17, a call ground electric door 18, and a call indicator lamp 19, where the equipment cooling electric door 11 is used to turn on the equipment cooling system, the equipment cooling indicator lamp 12 is turned on when the equipment cooling system fails, and after the equipment cooling electric door 11 is placed in an alternate position (ALTN), if the alternate equipment cooling system operates normally, the equipment cooling indicator lamp 12 is turned off. Normally, the emergency exit light switch 13 is protected by an external electric door cover and is arranged in an ARMED position, when the emergency exit light switch 13 is arranged in an OFF position, the emergency exit light pilot lamp 14 is not lightened, and when the electric door is arranged in an ON position, the cockpit does not have indication. The smoke prohibition electric door 15 and the safety belt tied electric door 16 are used for controlling a smoke prohibition lamp and a safety belt tied lamp of the passenger cabin, and the cockpit has no indication. The crew call electric gate 17 and the ground call electric gate 18 are electric gates used when calling outside people, and the cockpit has no response indication. The call indicator lamp 19 is intended to be lit when an outside person calls the cockpit, there is no relevant function on the simulator, but the lamp is still designed and can be lit by pressing.

Referring to fig. 8, the engine control panel 190 includes an ignition selection switch 191 and an engine start switch 192. The IGN L gear of the ignition selection electric valve 191 selects a left igniter for two engines, the IGN R gear selects a right igniter for the two engines, and the BOTH selects two ignitions for the two engines. The OFF position of the engine start switch 192 is such that the ignition actuator is normally OFF and does not ignite in flight, but the EEC (electronic engine control) will auto-ignite when it senses a possible combustion interruption (flame out) condition; the GRD gear is normally started, when the GRD gear is started, a starter valve is opened, after a starting handle is lifted, high-energy ignition is provided by a selected ignition relay, and when N2 is more than 56%, the starting switch automatically rebounds to an OFF position; the CONT gear unit is used during takeoff, landing and approach, and the selected igniter provides ignition when the engine is in a slow vehicle working state; in the FLT range, the EEC (electronic engine control unit) forces double ignition without using the position information of the ignition select switch. To the function that the automatic OFF position that rebounds of start switch, real aircraft use be that solenoid comes to realize, when N2 reached 56%, EEC (electronic engine control assembly) provided an electrical signal and made solenoid work, and solenoid work provides an electromagnetism suction, makes start switch get back to the OFF position, because the solenoid cost of realizing the function is higher, the utility model discloses a lower steering wheel of cost realizes this function: the electric signal that EEC provided drives the steering wheel motion, and steering wheel rotation drive a manipulator, the manipulator is direct with the electric door drive to OFF position, this design cost is lower easily to be realized and the reliability is higher.

Referring to fig. 9, the warming control panel 80 includes windshield overheating lamps 81, windshield warming lamps 82, windshield warming electric gates 83, windshield warming test electric gates 84, pitot tube warming lamps 85 and pitot tube warming control electric gates 86, wherein four windshield warming electric gates 83 control warming of two front windshields and two side windshields of the cockpit, four windshield warming lamps 82 respectively indicate a state of warming the four windshields, and four windshield overheating lamps 81 indicate a state of warming the four windshields; the windshield warming TEST switch 84 is set at the POWR TEST position to turn on the four windshield warming lamps 82, and the windshield warming TEST switch 84 is set at the OVHT position to turn on the four windshield overheating lamps 81. A. The two pitot tube heating control electric gates 86 respectively control the heating of the four pitot tubes at the left and the right, and the four pitot tube heating lamps 85 at the left and the right respectively indicate the corresponding pitot tube heating states.

Referring to fig. 10, the anti-icing control panel 90 includes a wing anti-icing shutter opening lamp 91, an engine cowl anti-icing shutter opening lamp 92, a cowl anti-icing lamp 93, a wing anti-icing control electric door 94, and an engine anti-icing control electric door 95, where the wing anti-icing control electric door 94 is configured to control opening and closing of the left and right wing anti-icing shutters, the wing anti-icing shutter opening lamp 91 is configured to indicate an opening and closing state of the corresponding wing anti-icing shutter, the engine anti-icing control electric door 95 is configured to control opening and closing of the engine cowl anti-icing shutter, the engine cowl anti-icing shutter opening lamp 92 is configured to indicate an opening and closing state of the corresponding cowl anti-icing shutter, and the cowl anti-icing lamp 93 is configured to indicate an operating state of the corresponding cowl anti-icing shutter.

Referring to fig. 11, the voice test panel 140 includes a zone microphone 141, a mute switch 142, a test switch 143, a status display lamp 144, and a handset 145. Because the simulator does not have cockpit recording requirements and functions, the panel only has a switch and an indicator lamp and has no corresponding functions.

Referring to fig. 12, the temperature control panel 100 includes a temperature selector 101, a temperature indication table 102, a zone temperature lamp 103, and a temperature control knob 104. The temperature selector 101 can select the temperatures of the air-conditioning air supply pipelines of the cockpit, the front and the rear cabins, the left and the right air-conditioning components and the front and the rear cabins to be used for the temperature indicator 102 to display corresponding temperature values; three temperature control knobs 104 are used for adjusting the temperature of the cockpit and the front and rear passenger cabins, and corresponding three zone temperature lamps 103 indicate whether the temperature of the three-cabin pipeline is overheated or not.

The power parameter display screen 31 of the power control panel 30 is an OLED display screen, which has a higher resolution, is different from the display of a nixie tube 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 utility model discloses engine starting electric door with true operation is felt, the innovative design has a steering wheel that can reach condition reset function, can make the starting electric door get back to the AUTO position when engine N2 rotational speed reaches 55%, and the innovative design condition reset function of driftage attenuator electric door 24 and wing anti-icing control electric door 94, a steering wheel has been used respectively, when reaching corresponding condition, the steering wheel actuates and makes driftage damping electric door or wing anti-icing control electric door get back to the OFF position, has low cost, easy control and have functions such as better flexibility and good stability.

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 (10)

1. An aircraft front roof simulator, characterized in that: the portable power supply comprises a case, be provided with preceding roof on the machine case, the below of preceding roof is provided with the board in a poor light, be provided with power module and control panel in the machine case, 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 preceding roof, still be provided with microprocessor on the control panel, microprocessor is used for communicating with preceding roof and data terminal.

2. An aircraft nose ceiling simulator as claimed in claim 1, wherein: the front top plate comprises a middle miscellaneous panel, wherein a flight control panel, a power supply control panel, an instrument selection panel, a standby power supply control panel, a fuel control panel, a generator control panel, a heating control panel, an anti-icing control panel, a temperature control panel, a hydraulic control panel, an air conditioner control panel, a cabin door display panel, a voice test panel, a height display panel and a pressurization control panel are respectively arranged on two sides of the middle miscellaneous panel, and a light control panel, an auxiliary power starting panel and an engine control panel are sequentially arranged at the bottom of the middle miscellaneous panel from left to right.

3. An aircraft nose ceiling simulator as claimed in claim 2, wherein: flight control panel includes flight control power gate, flight control low pressure lamp, flight spoiler power gate, driftage attenuator power gate and driftage attenuator lamp, the flight control power gate is used for controlling reserve hydraulic pump and opens reserve rudder and shuts OFF the valve, flight control low pressure lamp is used for lighting when system hydraulic pressure is low, the flight spoiler power gate is used for control system pressure to supply flight spoiler system, the driftage attenuator power gate is used for when flight relevant system is unsatisfied, and the driftage damping is thrown OFF, realizes through steering wheel and permanent magnet cooperation that automatic OFF position of rebounding back, the driftage attenuator lamp is used for lighting when the automatic OFF position of rebounding back of driftage attenuator power gate.

4. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the power control panel comprises a power parameter display screen, a storage battery discharge indicator lamp, a power conversion component lamp, an electric lamp, a maintenance electric door, a direct current selection electric door, a storage battery electric door, an alternating current selection electric door, a cabin power supply and an entertainment system power switch electric door, wherein the power parameter display screen adopts an OLED display screen for displaying direct current voltage parameters, alternating current voltage and frequency parameters and fault codes, the storage battery discharge indicator lamp is used for indicating the discharge state of a storage battery, the power conversion component lamp is used for being lightened when the system detects the fault of the power conversion component, the electric lamp is used for being lightened when the system detects the fault of the electrical system, the maintenance electric door is used for maintaining the power system, the direct current selection electric door is used for selecting a display source of direct current parameters on the power parameter display screen, and the storage battery electric door is used for switching on and off the storage battery, the alternating current selection electric door is used for selecting a display source of alternating current parameters on the power supply parameter display screen, and the cabin power supply and entertainment system power supply switch electric door is used for controlling a power supply in a cabin and a power supply of a cabin entertainment system.

5. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the fuel control panel includes that engine valve closes pilot lamp, wing spar valve pilot lamp, fuel and strains bypass pilot lamp, handing over valve pilot lamp and fuel temperature indicator, engine valve closes the state that the pilot lamp is used for instructing the interior fuel of engine and shuts off the valve, wing spar valve pilot lamp is used for instructing the state of engine wing spar valve, the bypass pilot lamp is strained to fuel is used for instructing the state that engine fuel was strained, handing over valve pilot lamp is used for instructing the position state that fuel system handed over the valve, fuel temperature indicator is controlled by the control board for according to user-defined temperature value of instructing.

6. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the standby power supply control panel comprises a standby power supply disconnection lamp, an engine drive indicating lamp, an engine drive disconnection electric door and a standby power supply electric door, wherein the standby power supply disconnection lamp is used for being turned on when the standby power supply electric door is in an OFF position, and the engine drive indicating lamp is used for being turned on when the engine drive disconnection electric door is opened.

7. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the middle miscellaneous item panel comprises an equipment cooling electric door, an equipment cooling indicator lamp, an emergency exit lamp switch, an emergency exit lamp non-preposition indicator lamp, a smoking prohibition electric door, a fastened safety belt electric door, a crew call electric door, a call ground electric door and a call indicator lamp, wherein the equipment cooling electric door is used for opening an equipment cooling system, the equipment cooling indicator lamp is lightened when the equipment cooling system fails, the emergency exit lamp non-preposition indicator lamp is used for lightening when the emergency exit lamp switch is arranged at an OFF position, the smoking prohibition electric door and the fastened safety belt electric door are used for controlling the prohibition smoke suction lamp and the fastened safety belt lamp of a passenger cabin, the crew call electric door and the call ground electric door are electric doors used when calling outside personnel, and the call indicator lamp is lightened when the outside personnel call a cockpit.

8. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the engine control panel includes ignition selection electric door and engine start electric door, the IGN L gear of ignition selection electric door selects left point firearm for two engines, and IGN R gear selects right point firearm for two engines, and BOTH selects two point firers for two engines, the engine start electric door is controlled by the control panel, realizes the automatic OFF position that rebounds through steering wheel and the cooperation of arm.

9. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the control panel that heats includes that the windscreen heats the lamp, the windscreen heats the electric door, the windscreen heats test electric door, pitot tube heats the lamp and pitot tube heats the control electric door, the windscreen heats the electric door and is used for controlling the heating of two front windshields and two side windshields in cockpit, the windscreen heats the lamp and is used for instructing the state that the windscreen heated, the windscreen is overheated the state that whether is used for instructing the windscreen to heat, the windscreen is heated test electric door and is used for testing the windscreen and heats the electric door, the pitot tube heats the heating that control electric door is used for controlling the pitot tube, the pitot tube is heated the lamp and is used for instructing the state that the pitot tube heated.

10. An aircraft nose ceiling simulator as claimed in claim 2, wherein: the anti-icing control panel comprises a wing anti-icing valve opening lamp, an engine fairing anti-icing valve opening lamp, a fairing anti-icing lamp, a wing anti-icing control electric door and an engine anti-icing control electric door, wherein the wing anti-icing control electric door is used for controlling the opening and closing of the left wing anti-icing valve and the right wing anti-icing valve, the wing anti-icing valve opening lamp is used for indicating the on-off state of the corresponding wing anti-icing valve, the engine anti-icing control electric door is used for controlling the opening and closing of the engine fairing anti-icing valve, the engine fairing anti-icing valve opening lamp is used for indicating the on-off state of the corresponding fairing anti-icing valve, and the fairing anti-icing lamp is used for indicating the working state of the corresponding fairing anti-icing valve.

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