Aircraft oil leakage simulation comprehensive training equipment

Abstract

The utility model discloses simulation comprehensive training equipment for airplane oil leakage. The simulation comprehensive training equipment comprises a first steel frame, a second steel frame, a top plate, an undercarriage cabin door, a cabin door folding and unfolding actuator cylinder, a cabin door lock mechanism, a control panel, an oil tank, a hydraulic system electric pump, a top plate hanging bracket, a simulation frame, a cabin door bypass valve and a cabin door selection valve. By adopting the airplane oil leakage simulation device, the simulation of the real maintenance environment of an airplane can be realized, the training function of maintenance skills related to the oil leakage of the airplane can be provided, and the capability of maintenance personnel for processing the oil leakage problem of the airplane can be cultivated and improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft safety, in particular to an aircraft oil leakage simulation comprehensive training device. Background Technique

[0002] Aircraft oil leakage, commonly known as "running, overflowing, dripping, and leaking", not only occupies a large amount of maintenance resources, causing a large maintenance burden, but also affects the safe operation and airworthiness maintenance of the aircraft, and even leads to unsafe events such as aircraft fires and explosions, in-flight engine shutdowns, gravity landing gear deployment, and aircraft occupying the runway. Therefore, aircraft oil leakage is a difficult and painful point in aircraft maintenance.

[0003] In the prior art, generally, some basic skills related to the maintenance of the hydraulic system (such as the disassembly, installation, and inspection of hard and soft pipes, etc.) are extracted and made into a bench for users to conduct basic skills training of the hydraulic system. However, it cannot provide a highly simulated real working environment of the aircraft and comprehensive training items, resulting in a certain difference between the skills obtained by the trainees during training and the actual requirements, and it is difficult to cultivate situational awareness. Content of the Utility Model

[0004] In order to solve the above problems, the utility model proposes an aircraft oil leakage simulation comprehensive training device, which can realize the simulation of the real maintenance environment of the aircraft and provide the training function of maintenance skills related to aircraft oil leakage, and is helpful to cultivate and improve the ability of maintenance personnel to handle aircraft oil leakage problems.

[0005] The embodiment of the utility model provides an aircraft oil leakage simulation comprehensive training device, including a first steel frame 1, a second steel frame 2, a top plate 3, a landing gear door 6, a door retraction actuator 7, a door lock mechanism 8, a control panel 25, a fuel tank 16, a hydraulic system electric pump 17, a top plate hanger 18, a simulation frame 26, a door bypass valve 23, and a door selection valve 24;

[0006] The top plate 3 is installed inside the first steel frame 1 and the second steel frame 2; the landing gear doors 6 are respectively installed outside the first steel frame 1 and the second steel frame 2; the landing gear doors 6 are actuated by the door retraction and extension actuating cylinder 7 installed thereon; the retracted position of the landing gear doors 6 is locked by the door lock mechanism 8 suspended from the tops of the first steel frame 1 and the second steel frame 2; the control panel 25 is installed on the surfaces of the first steel frame 1 and the second steel frame 2; the fuel tank 16 is installed above the simulation frame 26; the hydraulic system electric pump 17 is installed inside the first steel frame 1 and adjacent to the simulation frame 26; the top plate hanger 18 is installed inside the top plate 3; the door bypass valve 23 is respectively installed on the tops of the first steel frame 1 and the second steel frame 2; the door selection valve 24 is installed in the middle of the simulation frame 26.

[0007] As one of the preferred solutions, the control panel 25 includes a hydraulic system servicing panel 12, and a hand pump 1201, a fuel filling valve 1202, a manual pressure relief valve 1203, a fuel tank inflation valve 1204, a retractable fuel filling handle 1205, a handle mounting bracket 1206, a fuel hose storage tank 1207 and a fuel gauge 1208 are installed inside the hydraulic system servicing panel 12;

[0008] The fuel filling valve 1202 is installed on the hand pump 1201; the manual pressure relief valve 1203 is used to relieve the pressure of the fuel tank; the retractable fuel filling handle 1205 is fixed on the two handle mounting brackets 1206 on both sides; the hose stored in the fuel hose storage tank 1207 is used to be installed on the fuel filling valve 1202; the fuel gauge 1208 is used to monitor the fuel filling volume.

[0009] As one of the preferred solutions, the control panel 25 includes a landing gear manual retraction and extension servicing panel 13, and two identical door retraction and extension handles are installed inside the landing gear manual retraction and extension servicing panel 13. The door retraction and extension handles include a left door retraction and extension handle 1301 and a right door retraction and extension handle 1302; the left door retraction and extension handle 1301 correspondingly controls the landing gear door outside the first steel frame 1, and the right door retraction and extension handle 1302 correspondingly controls the landing gear door outside the second steel frame 2; the actuation methods of the door retraction and extension handles are the same.

[0010] As one of the preferred solutions, the control panel 25 includes a touch screen control panel 14, and a first touch screen 1401 and each page switching button 1402 are installed inside the touch screen control panel 14;

[0011] The touch - screen control panel 14 selects different display pages through the respective page - switching buttons 1402 and displays them on the first touch - screen 1401, and performs touch - screen operations within the corresponding display pages.

[0012] As one of the preferred solutions, the control panel 25 includes a touch - screen display and landing - gear door control handle panel 15. A second touch - screen 1501 and a landing - gear door control handle 1502 are installed inside the touch - screen display and landing - gear door control handle panel 15.

[0013] The touch - screen display and landing - gear door control handle panel 15 selects different second display pages for display through the buttons inside the second touch - screen 1501, and performs touch - screen operations within the second display pages; the landing - gear door 6 is controlled to be retracted or lowered by moving the landing - gear door control handle 1502 to the retracted position or the lowered position.

[0014] As one of the preferred solutions, a high - pressure main pipe 1801, a pressure sensor 1802, an electric - pump outlet pressure switch 1803, a return - oil filter 1804, a priority valve 1805, a sampling valve 1806, and a high - pressure main - pipe mounting base 1807 are installed inside the top - plate hanger 18.

[0015] The high - pressure main pipe 1801 is installed above the high - pressure main - pipe mounting base 1807, the pressure sensor 1802 and the electric - pump outlet pressure switch 1803 are installed above the high - pressure main pipe 1801, and the priority valve 1805 and the sampling valve 1806 are installed on the side of the high - pressure main pipe 1801.

[0016] As one of the preferred solutions, several independent toolboxes 19 are respectively provided on the inner lower layers of the first steel frame 1 and the second steel frame 2. The toolboxes 19 are used to store virtual - reality devices, disassembly and assembly maintenance tools, printers, or host integrated circuits.

[0017] As one of the preferred solutions, the device further includes: a bolt 4 and universal wheels 5.

[0018] Among them, the top - plate 3 is connected to the inner sides of the first steel frame 1 and the second steel frame 2 through the bolt 4; the same universal wheels 5 are respectively installed at both ends of the bottom of the first steel frame 1 and the second steel frame 2.

[0019] As one of the preferred solutions, the device is a bolt - shaped three - dimensional structure, and the various components of the device are hydraulically connected by means of quick - release joints.

[0020] Compared with the prior art, in the present utility model, corresponding components of the aircraft are arranged in corresponding simulation areas within the device, and key components are set in the simulation areas, which realistically simulates the composition and component installation of the system related to aircraft oil leakage, can realize the simulation of the real maintenance environment of the aircraft and provide the training function for the maintenance skills related to aircraft oil leakage, and helps to cultivate and improve the ability of maintenance personnel to handle aircraft oil leakage problems. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic structural diagram of an aircraft oil leakage simulation comprehensive training device provided by the present utility model;

[0022] Figure 2 is a front view of the hydraulic system servicing panel provided by the present utility model;

[0023] Figure 3 is a front view of the landing gear manual retraction servicing panel provided by the present utility model;

[0024] Figure 4 is a front view of the touch screen control panel provided by the present utility model;

[0025] Figure 5 is a front view of the touch screen display and landing gear door control handle panel provided by the present utility model;

[0026] Figure 6 is a schematic diagram of the interior of the top plate hanger provided by the present utility model;

[0027] Figure 7 is a schematic diagram of the hydraulic system control principle provided by the present utility model;

[0028] Figure 8 is an integrated circuit diagram of the hydraulic system control provided by the present utility model;

[0029] Figure 9 is an integrated circuit diagram of the landing gear door retraction system control provided by the present utility model;

[0030] Figure 10 is a schematic diagram of the landing gear door retraction system control principle provided by the present utility model.

[0031] In the figure: 1 - First steel frame; 2 - Second steel frame; 3 - Top plate; 4 - Bolt; 5 - Universal wheel; 6 - Landing gear hatch; 7 - Hatch retraction actuator; 8 - Hatch lock mechanism; 9 - LCD touch screen TV; 10 - First brand logo; 11 - Second brand logo; 12 - Hydraulic system servicing panel; 13 - Landing gear manual retraction servicing panel; 14 - Touch screen control panel; 15 - Touch screen display and landing gear hatch control handle panel; 16 - Fuel tank; 17 - Electric pump of hydraulic system; 18 - Hanger on top plate; 19 - Toolbox; 20 - Keel beam simulation frame; 21 - Simulation frame of front wall of landing gear compartment section; 22 - Simulation frame of rear wall of landing gear compartment section; 23 - Hatch bypass valve; 24 - Hatch selection valve; 25 - Control panel; 26 - Simulation frame; 1801 - High pressure main pipe 1801; 1802 - Pressure sensor 1802; 1803 - Electric pump outlet pressure switch; 1804 - Return oil filter; 1805 - Priority valve; 1806 - Sampling valve; 1807 - Mounting base of high pressure main pipe; 1201 - Hand pump; 1202 - Fuel filling valve; 1203 - Manual pressure relief valve; 1204 - Fuel tank inflation valve; 1205 - Telescopic fuel filling handle; 1206 - Handle mounting bracket; 1207 - Fuel hose storage tank; 1208 - Fuel gauge; 1301 - Left hatch retraction handle; 1302 - Right hatch retraction handle; 1401 - First touch screen; 1402 - Page switching buttons; 1501 - Second touch screen; 1502 - Landing gear retraction control handle; D1 - Low pressure switch of fuel tank air; K1 - Control switch of electric pump; S1 - Fuel tank temperature and oil level sensor; R1 - Fuel tank overheat and low pressure relay of air; R2 - Low pressure relay of electric pump outlet; R3 - Control contactor of electric pump; R4 - First time delay relay; R5 - Second time delay relay; P1 - Left hatch up proximity switch; P2 - Right hatch up proximity switch. Detailed implementation manners

[0032] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0033] In the description of this application, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of this application, unless otherwise stated, the meaning of "a plurality" is two or more.

[0034] In the description of the present application, it should be noted that, unless otherwise clearly defined and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0035] In the description of the present application, it should be noted that, unless otherwise defined, all the technical and scientific terms used in the present utility model have the same meanings as those commonly understood by those skilled in the technical field to which the present application pertains. The terms used in the description of the present utility model are only for the purpose of describing specific embodiments, and are not intended to limit the present utility model. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0036] See Figure 1 , an aircraft oil leakage simulation comprehensive training device is provided in an embodiment of the present utility model, including: a first steel frame 1, a second steel frame 2, a top plate 3, a landing gear door 6, a door retraction actuator 7, a door lock mechanism 8, a control panel 25, a fuel tank 16, a hydraulic system electric pump 17, a top plate hanger 18, a simulation frame 26, a door bypass valve 23, and a door selection valve 24;

[0037] The top plate 3 is installed inside the first steel frame 1 and the second steel frame 2; the landing gear doors 6 are respectively installed outside the first steel frame 1 and the second steel frame 2; the landing gear doors 6 are actuated by the door retraction actuators 7 installed thereon; the retracted position of the landing gear doors 6 is locked by the door lock mechanism 8 suspended from the tops of the first steel frame 1 and the second steel frame 2; the control panel 25 is installed on the surfaces of the first steel frame 1 and the second steel frame 2; the fuel tank 16 is installed above the simulation frame 26; the hydraulic system electric pump 17 is installed inside the first steel frame 1 and adjacent to the simulation frame 26; the top plate hanger 18 is installed inside the top plate 3; the door bypass valves 23 are respectively installed on the tops of the first steel frame 1 and the second steel frame 2; the door selection valve 24 is installed in the middle of the simulation frame 26.

[0038] In a specific implementation, the first steel frame 1 and the second steel frame 2 are separated by the top plate 3. The devices in the fuel tank 16, the hydraulic system electric pump 17, and the top plate hanger 18 constitute a set of hydraulic systems. The door selection valve 24 is used to control the hydraulic on-off and hydraulic direction of the landing gear doors 6.

[0039] In specific implementation, by arranging components corresponding to the aircraft within the device in corresponding simulation areas and setting corresponding key components in the simulation areas, the composition and component installation conditions of the system related to aircraft oil leakage are simulated more realistically, enabling the simulation of the actual maintenance environment of the aircraft and providing training functions for maintenance skills related to aircraft oil leakage, which helps to cultivate and improve the ability of maintenance personnel to handle aircraft oil leakage problems.

[0040] As an improvement to the above solution, the simulation rack 26 includes a keel beam simulation rack 20, a front wall simulation rack 21 of the landing gear compartment, and a rear wall simulation rack 22 of the landing gear compartment;

[0041] Among them, the keel beam simulation rack 20 is installed at the middle position between the first steel frame 1 and the second steel frame 2; both ends of the keel beam simulation rack 20 are respectively connected to the front wall simulation rack 21 of the aircraft landing gear compartment and the rear wall simulation rack 22 of the landing gear compartment. The front wall simulation rack 21 of the landing gear compartment is installed at one end inside the first steel frame 1 close to the outer door, and the rear wall simulation rack 22 of the landing gear compartment is installed at one end inside the second steel frame 2 close to the outer door.

[0042] In specific implementation, the fuel tank (16) is installed above the keel beam simulation rack (20); the electric pump (17) of the hydraulic system is installed inside the first steel frame (1) and adjacent to the keel beam simulation rack (20); the door selection valve (24) is installed in the middle of the keel beam simulation rack (20).

[0043] See Figure 2 , as an improvement to the above solution, the control panel 25 includes a hydraulic system servicing panel 12. The hydraulic system servicing panel 12 is internally installed with a hand pump 1201, a fuel filling valve 1202, a manual pressure relief valve 1203, a fuel tank inflation valve 1204, a retractable fuel filling handle 1205, a handle mounting bracket 1206, a fuel hose storage tank 1207, and a fuel gauge 1208;

[0044] The fuel filling valve 1202 is installed on the hand pump 1201; the manual pressure relief valve 1203 is used to relieve the pressure of the fuel tank; the retractable fuel filling handle 1205 is fixed to the two handle mounting brackets 1206 on both sides; the hose stored in the fuel hose storage tank 1207 is used to be installed on the fuel filling valve 1202; the fuel gauge 1208 is used to monitor the fuel filling volume.

[0045] In a specific implementation, the hydraulic system servicing panel 12 is used for refueling service and fuel tank pressure relief service of the hydraulic system, specifically as follows: Open the handle mounting bracket 1206, take out the retractable refueling handle 1205 and install it on the hand pump 1201. At the same time, take out the hose stored in the refueling hose storage tank 1207 and install it on the refueling valve 1202. Repeatedly shake the retractable refueling handle 1205 back and forth to refuel the fuel tank 16, and monitor the refueling amount through the fuel gauge 1208. Press and rotate the manual pressure relief valve 1203 to relieve the pressure of the fuel tank 16.

[0046] See Figure 3 , as an improvement to the above solution, the control panel 25 includes a landing gear manual retraction servicing panel 13. Two identical hatch retraction handles are installed in the landing gear manual retraction servicing panel 13. The hatch retraction handles include a left hatch retraction handle 1301 and a right hatch retraction handle 1302; the left hatch retraction handle 1301 correspondingly controls the landing gear hatch outside the first steel frame 1, and the right hatch retraction handle 1302 correspondingly controls the landing gear hatch outside the second steel frame 2; the actuation methods of the hatch retraction handles are the same.

[0047] In a specific implementation, taking the left hatch retraction handle 1301 as an example, its actuation method is specifically as follows: Press the protruding button on the left hatch retraction handle 1301 to move the left hatch retraction handle. The left hatch retraction handle actuates the bypass hydraulic oil circuit of the hatch bypass valve 23 on the first steel frame 1 through a steel cable, and the landing gear hatch 6 can be lowered by gravity. When the hydraulic system is pressurized, rotate the left hatch retraction handle 1301 until the protruding button on it pops out, and the landing gear hatch 6 is retracted to the locked position through the hatch retraction actuator 7 and locked by the hatch lock mechanism 8.

[0048] See Figure 4 , as an improvement to the above solution, the control panel 25 includes a touch screen control panel 14. A first touch screen 1401 and various page switching buttons 1402 are installed in the touch screen control panel 14;

[0049] The touch screen control panel 14 selects different display pages through the various page switching buttons 1402 and displays them on the first touch screen 1401, and performs touch screen operations within the corresponding display pages.

[0050] In specific implementation, the first display page includes, but is not limited to: a hydraulic boost page, a hydraulic system page, a landing gear door page, an air-ground configuration operation page, a warning sign operation page, replacement part timing, a torque monitoring page, a fault simulation selection page, a dynamic hydraulic operation principle page, a dynamic internal hydraulic page of important components, and a hydraulic fluid-related skills learning page.

[0051] After the hydraulic system service panel 12 is used to relieve the pressure of the fuel tank 16, a corresponding hydraulic system page will pop up on the first touch screen 1401 of the touch screen control panel 14, and a low fuel tank pressure warning will pop up within the page.

[0052] During the process of using the landing gear manual retraction and extension service panel to retract and extend the landing gear door, the position change of the landing gear door 6 can be observed through the corresponding landing gear door page in the first touch screen 1401 of the touch screen control panel 14.

[0053] See Figure 5 As an improvement to the above solution, the control panel 25 includes a touch screen display and landing gear door control handle panel 15, and a second touch screen 1501 and a landing gear door control handle 1502 are installed in the touch screen display and landing gear door control handle panel 15;

[0054] The touch screen display and landing gear door control handle panel 15 selects different second display pages for display through the buttons in the second touch screen 1501 and performs touch screen operations within the second display page; the landing gear door 6 is controlled to retract and extend by moving the landing gear door control handle 1502 to the retracted position or the extended position.

[0055] In specific implementation, the second display page includes, but is not limited to, a dynamic hydraulic operation principle page, a dynamic internal hydraulic page of important components, and a hydraulic fluid-related skills learning page.

[0056] The control logic for moving the landing gear door control handle 1502 to the retracted position and the extended position is the same. Taking moving to the retracted position as an example, specifically: the landing gear door control handle 1502 releases the handle lock according to the air signal given by the air-ground signal source, and then the landing gear door control handle 1502 can be moved to the retracted position. When the landing gear door control handle 1502 is moved to the retracted position, the landing gear door 6 automatically opens through the door selection valve 24 to connect to the door retraction and extension actuator 7, and after a three-second delay, the landing gear door 6 automatically closes to the locked position of the door lock mechanism 8.

[0057] The landing gear door 6 can also be manually retracted and extended through a manual retraction and extension handle.

[0058] See Figure 6, as an improvement to the above solution, a high-pressure main pipe 1801, a pressure sensor 1802, an electric pump outlet pressure switch 1803, an oil return filter 1804, a priority valve 1805, a sampling valve 1806, and a high-pressure main pipe mounting base 1807 are installed inside the top plate hanger 18;

[0059] The high-pressure main pipe 1801 is installed above the high-pressure main pipe mounting base 1807, the pressure sensor 1802 and the electric pump outlet pressure switch 1803 are installed above the high-pressure main pipe 1801, and the priority valve 1805 and the sampling valve 1806 are installed on the side of the high-pressure main pipe 1801.

[0060] In a specific implementation, the electric pump 17 of the hydraulic system provides a pressure source with a working pressure of 3000 PSI. The maximum oil volume of the fuel tank 16 is 18 L, which provides a hydraulic oil working medium for the hydraulic system.

[0061] See Figure 7 , the equipment in the top plate hanger 18 is used to operate and monitor the hydraulic system. Specifically: the high-pressure oil is distributed through the high-pressure main pipe 1801, and the electric pump outlet pressure switch 1803 monitors the outlet pressure of the electric pump 17 of the hydraulic system. When the outlet pressure of the electric pump 17 of the hydraulic system is lower than the threshold value (for example, 1450 PSI), a low-pressure warning of the system is displayed on the hydraulic system page. The pressure sensor 1802 senses the system pressure in real time and displays it on the hydraulic system page. The priority valve 1805 controls the hydraulic flow rate and shuts off its downstream users when the flow rate exceeds the set value. The user is the landing gear door retraction system. The oil return filter 1804 filters the impurities in the system return oil.

[0062] See Figure 1 , as an improvement to the above solution, several independent toolboxes 19 are respectively provided on the lower layers inside the first steel frame 1 and the second steel frame 2. The toolboxes 19 are used to store virtual reality devices, disassembly and maintenance tools, printers, or host integrated circuits.

[0063] In a specific implementation, the virtual reality device realizes the virtual operation functions of learning and simulating actual operations and being able to conduct project assessments for each training project by simulating the control panels of various systems in the aircraft cockpit, the circuit breaker panel, the pipelines and components in the landing gear compartment, the engine, the aircraft exhaust main pipe, the dry bay of a certain type of aircraft wing, etc. The training projects include but are not limited to: basic hydraulic service training, basic hydraulic construction training, important hydraulic construction skills training, engine oil component construction skills training, system test training, and hydraulic pipeline repair skills training.

[0064] The host integrated circuit includes a hydraulic system control integrated circuit and a landing gear door retraction and extension system control integrated circuit.

[0065] See Figure 8 , in the hydraulic system control integrated circuit, the electric pump control switch K1 is virtualized to the touch screen control hydraulic boost page. Click the electric pump control switch K1 once, and the ON light on its switch lights up, indicating that the electric pump 17 of the hydraulic system is powered on and running, and the hydraulic system starts to boost. When the hydraulic system monitors a fault, the FAULT light on the switch lights up, indicating that a fault has occurred in the hydraulic system. The fuel tank overheat and low air pressure relay R1, the electric pump outlet low pressure relay R2, and the electric pump control contactor R3 are all integrated into the hydraulic system control integrated circuit.

[0066] Specifically, when the fuel tank temperature and oil level sensor S1 senses that the fuel tank hydraulic oil temperature ≥ 100 ± 2.2 deg.C, a warning is triggered, and the fault is displayed on the hydraulic system page of 1401. The system pressure indication is amber (pressure less than 1450 PSI), the system identification (green) indication is white, and the system arrow indication is green. When the fuel tank low air pressure switch D1 senses that the fuel tank air pressure drops to less than 2.5 ± 0.1 bar (37 ± 1.45 psia) absolute pressure (1.5 ± 0.1 bar (22 ± 1.45 psig) relative pressure), the contact of the fuel tank low air pressure switch D1 closes. A single tone warning sounds, the FAULT light on the electric pump control switch K1 lights up, and the corresponding warning is displayed on the hydraulic system page.

[0067] See Figure 9 , in the landing gear door retraction and extension system control integrated circuit, the landing gear door control handle 1502 releases the handle lock according to the air signal given by the air / ground signal source, and then the landing gear door control handle 1502 can be moved to the retracted position. The air / ground signal is integrated into the landing gear door retraction and extension system control integrated circuit by the air / ground configuration circuit breaker. Select the corresponding page through the button on the touch screen control panel 14 to perform the air configuration operation. After the operation is completed, an air signal is given to release the control handle lock. The left door retraction proximity switch P1 and the right door retraction proximity switch P2 respectively sense the positions of the corresponding landing gear doors 6. When the position of the landing gear door 6 is inconsistent with the control handle position or the landing gear door 6 is moving, the door indication on the landing gear door page shows amber.

[0068] Specifically, by selecting the ground / air configuration page through the buttons on the touch control panel 14, the corresponding circuit breaker is pulled out, the lock of the landing gear door control handle 1502 is released, and the handle is moved from the down position (DOWN position) to the retracted position (UP position). At this time, the first delay relay R4 operates, the door selection valve 24 opens to connect the hydraulic pressure, and the landing gear door 6 opens. After six seconds, the first delay relay R4 disconnects, the second delay relay R5 operates, the door selection valve 24 closes to connect the hydraulic pressure, and the landing gear door 6 closes. After six seconds, the second delay relay R5 disconnects.

[0069] See Figure 10 , the door selection valve 24 connects the downstream retraction or extension hydraulic circuit according to the signal given by the control integrated circuit of the landing gear door retraction and extension system. The hydraulic oil passes through the door bypass valve 23 and then supplies hydraulic pressure to the door lock mechanism 8 for unlocking. After unlocking, the landing gear door retraction and extension actuator 7 connects to the retraction or extension hydraulic circuit, thereby actuating the landing gear door 6.

[0070] The main integrated circuit and its supporting software are mainly used for: collecting the parameters of the hydraulic system and the landing gear door retraction and extension system, monitoring and supporting the operation of each main system of the host, and displaying the system principles and dynamic diagrams related to oil leakage skills, etc.

[0071] Specifically, the main integrated circuit and its supporting software are used to collect parameters such as the position of the landing gear door, the pressure of the hydraulic system, the temperature of the hydraulic oil, the pressure of the pressurized air in the fuel tank, and the oil level in the fuel tank, so as to realize dynamic control, monitoring and status display of the system; when a fault occurs, it can trigger corresponding fault warnings and alerts, and is also used to realize fault simulation according to the fault logic; it is also used to realize actual operations such as pressurization, pulling out the circuit breaker and hanging warning signs, switching of each display or control interface, monitoring the installation torque of some specified pipeline joints, and timing of actual replacement parts; it is also used to display the dynamic changes of the internal hydraulic actuation principle of the system, the dynamic changes of the hydraulic on / off of the main components, etc.; it is also used to monitor the installation torque of specified pipeline joints, time the actual replacement of parts, virtual reality simulation inspection, etc. to realize skill assessment and scoring.

[0072] In the specific implementation, by setting the corresponding aircraft components in the equipment in the corresponding simulation area, setting the corresponding key components in the simulation area, and simulating various system forms through external system control, through virtual reality simulation operation, and through the actual operation of hydraulic component disassembly and assembly, the composition and component installation of the system related to aircraft oil leakage are simulated more realistically, thereby realizing the learning and training of maintenance personnel. The environment is highly realistic and can be used to assess the maintenance personnel's mastery of aircraft oil-related issues, and their awareness of standardized construction and safe maintenance of oil-related system processing, providing a numerical basis for skill rating, accelerating the cultivation of maintenance personnel's aircraft maintenance situational awareness, and improving maintenance personnel's aircraft oil leakage problem handling skills.

[0073] As an improvement of the above scheme, the device also includes a latch 4 and a universal pulley 5; wherein the top plate 3 is connected to the inner sides of the first steel frame 1 and the second steel frame 2 through the latch 4; the same universal pulley 5 is respectively installed at both ends of the bottom of the first steel frame 1 and the second steel frame 2.

[0074] In a specific implementation, the first steel frame 1 and the second steel frame 2 can be separated independently, and after separation, they can be flexibly moved through the universal pulley, or locked in place. Therefore, the entire aircraft oil leakage simulation comprehensive training device after assembly can be flexibly moved, or locked in place.

[0075] As an improvement of the above solution, the device is a bolt-shaped three-dimensional structure, and the various components of the device are hydraulically connected by means of quick-release joints.

[0076] As an improvement of the above solution, the device also includes a liquid crystal touch screen TV 9 and a graphic board of a brand logo.

[0077] See also Figure 1 The LCD touch screen TV 9 is installed on the surface of the device; the brand logo boards, including the first brand logo 10 and the second brand logo 11, are also installed on the surface of the device.

[0078] The above is only a preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto. It should be pointed out that for those skilled in the art, several equivalent obvious variations and / or equivalent substitutions can be made without departing from the technical principle of the present invention. These obvious variations and / or equivalent substitutions should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft oil leakage simulation comprehensive training device, characterized in that, Including: A first steel frame (1), a second steel frame (2), a top plate (3), a landing gear door (6), a door retraction actuator (7), a door lock mechanism (8), a control panel (25), a fuel tank (16), an electric pump for the hydraulic system (17), a top plate hanger (18), a simulation frame (26), a door bypass valve (23), and a door selection valve (24); The top plate (3) is installed inside the first steel frame (1) and the second steel frame (2); the landing gear doors (6) are respectively installed outside the first steel frame (1) and the second steel frame (2); the landing gear doors (6) are actuated by the door retraction actuators (7) installed thereon; the retracted position of the landing gear doors (6) is locked by the door lock mechanism (8) suspended from the tops of the first steel frame (1) and the second steel frame (2); the control panel (25) is installed on the surfaces of the first steel frame (1) and the second steel frame (2); the fuel tank (16) is installed above the simulation frame (26); the electric pump for the hydraulic system (17) is installed inside the first steel frame (1) and adjacent to the simulation frame (26); the top plate hanger (18) is installed inside the top plate (3); the door bypass valves (23) are respectively installed on the tops of the first steel frame (1) and the second steel frame (2); the door selection valve (24) is installed in the middle of the simulation frame (26).

2. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, wherein, The control panel (25) includes a hydraulic system servicing panel (12), and a hand pump, a fueling valve, a manual pressure relief valve, a fuel tank inflation valve, a retractable fueling handle, a handle mounting bracket, a fuel hose storage tank, and a fuel gauge are installed inside the hydraulic system servicing panel (12); The fueling valve is installed on the hand pump; the manual pressure relief valve is used to relieve the pressure of the fuel tank; the retractable fueling handle is fixed to the two handle mounting brackets on both sides; the hose stored in the fuel hose storage tank is used to be installed on the fueling valve; the fuel gauge is used to monitor the fueling volume.

3. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that, The control panel (25) includes a landing gear manual retraction servicing panel (13), and two identical door retraction handles are installed inside the landing gear manual retraction servicing panel (13), and the door retraction handles include a left door retraction handle and a right door retraction handle; the left door retraction handle correspondingly controls the landing gear door outside the first steel frame (1), and the right door retraction handle correspondingly controls the landing gear door outside the second steel frame (2); the actuation methods of the door retraction handles are the same.

4. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that, The control panel (25) includes a touch screen control panel (14), and a first touch screen and various page switching buttons are installed inside the touch screen control panel (14); The touch screen control panel (14) selects different display pages to be displayed on the first touch screen through the various page switching buttons, and performs touch screen operations within the corresponding display pages.

5. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that, The control panel (25) includes a touch screen display and landing gear door control handle panel (15), and a second touch screen and a landing gear door control handle are installed in the touch screen display and landing gear door control handle panel (15). The touch screen display and landing gear door control handle panel (15) selects different second display pages for display through the buttons in the second touch screen and performs touch screen operations within the second display page; the landing gear door (6) is controlled to retract or extend by moving the landing gear door control handle to the retracted position or the extended position.

6. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that, A high-pressure main pipe, a pressure sensor, an electric pump outlet pressure switch, an oil return filter, a priority valve, a sampling valve, and a high-pressure main pipe mounting base are installed in the top plate hanger (18). The high-pressure main pipe is installed above the high-pressure main pipe mounting base, the pressure sensor and the electric pump outlet pressure switch are installed above the high-pressure main pipe, and the priority valve and the sampling valve are installed on the side of the high-pressure main pipe.

7. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that Several independent toolboxes (19) are respectively provided on the inner lower layers of the first steel frame (1) and the second steel frame (2), and the toolboxes (19) are used for storing virtual reality devices, disassembly and maintenance tools, printers or host integrated circuits.

8. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that, The simulation frame (26) includes a keel beam simulation frame (20), a front wall simulation frame (21) of the landing gear compartment section, and a rear wall simulation frame (22) of the landing gear compartment section. Among them, the keel beam simulation frame (20) is installed at the middle position between the first steel frame (1) and the second steel frame (2); both ends of the keel beam simulation frame (20) are respectively connected to the front wall simulation frame (21) of the aircraft landing gear compartment section and the rear wall simulation frame (22) of the landing gear compartment section. The front wall simulation frame (21) of the landing gear compartment section is installed at one end of the first steel frame (1) close to the outer door, and the rear wall simulation frame (22) of the landing gear compartment section is installed at one end of the second steel frame (2) close to the outer door.

9. The aircraft oil leakage simulation comprehensive training equipment according to claim 1, characterized in that It also includes a bolt (4) and a universal pulley (5). Among them, the top plate (3) is connected to the inner sides of the first steel frame (1) and the second steel frame (2) through the bolt (4); the same universal pulleys (5) are respectively installed at both ends of the bottom of the first steel frame (1) and the second steel frame (2).

10. A comprehensive training device for aircraft oil leakage simulation according to claim 1, characterized in that, The device is a bolt-shaped three-dimensional structure, and the various components of the device are hydraulically connected by means of quick-release joints.

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