CN114360323A - Method for separating simulation engine and displaying EGT (expanded text transfer) red box on flight simulator - Google Patents
Method for separating simulation engine and displaying EGT (expanded text transfer) red box on flight simulator Download PDFInfo
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- CN114360323A CN114360323A CN202210025406.XA CN202210025406A CN114360323A CN 114360323 A CN114360323 A CN 114360323A CN 202210025406 A CN202210025406 A CN 202210025406A CN 114360323 A CN114360323 A CN 114360323A
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- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000004088 simulation Methods 0.000 title claims abstract description 21
- 238000012546 transfer Methods 0.000 title description 2
- 238000000926 separation method Methods 0.000 claims abstract description 31
- 230000005484 gravity Effects 0.000 claims description 16
- 230000003213 activating effect Effects 0.000 claims description 11
- 239000000446 fuel Substances 0.000 claims description 10
- 239000000295 fuel oil Substances 0.000 claims description 9
- 238000012545 processing Methods 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 6
- 230000004913 activation Effects 0.000 claims description 3
- 238000007689 inspection Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000004044 response Effects 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 2
- 230000008569 process Effects 0.000 description 4
- 238000012549 training Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000011514 reflex Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention provides a method for separating a simulated engine and displaying an EGT red box on a flight simulator, wherein a simulation system of the flight simulator comprises flight guidance and control, an aerodynamic model, a power system, a display system and other systems, the power system comprises an engine and an APU, the engine comprises an engine model, an engine interface, an engine fault scene, engine sound and engine vibration, and the engine fault scene comprises engine separation, engine red box display and other fault scenes. The invention has the advantages of providing various fault scenes and increasing the functions of the flight simulator.
Description
Technical Field
The invention belongs to the field of flight simulators, and particularly relates to a method for simulating engine separation and EGT red box display on a flight simulator.
Background
A flight simulator is a system that reproduces or simulates the driving feel of an aircraft as realistically as possible. The flight simulator is widely applied to design and research and development by the aviation industry, and can vividly reflect the aircraft attitude, the aircraft movement, the instrument prompt, the environmental change, the surrounding sound, the physiological reaction and the like which are seen, heard and touched when a pilot operates a real aircraft in the air to the pilot, thereby obtaining the actual effect of researching flight or training flight.
The existing flight simulator scene mainly aims at common faults or states in the flight process, has no specific scene for faults with low probability of engine separation, and is not provided by a third-party supplier for faults displayed by an engine EGT red box, and a pilot lacks emergency treatment experience for low probability faults in the training process.
Disclosure of Invention
The invention aims to provide a method for separating a simulation engine and displaying an EGT (expanded message Table) red box on a flight simulator, which comprises a plurality of fault scenes and increases the functions of the flight simulator, and is particularly suitable for the fault environment simulation work of the flight simulator.
The technical scheme of the invention is as follows: the method comprises the steps that EGT is the exhaust temperature of an engine, a simulation system of the flight simulator comprises flight guidance and control, an aerodynamic model, a power system, a display system and other systems, the power system comprises the engine and an APU, the engine comprises an engine model, an engine interface, an engine fault scene, engine sound and engine vibration, and the engine fault scene comprises engine separation, engine red box display and other fault scenes.
Further, the simulation method of engine separation comprises:
the method comprises the following steps: activating engine disconnect, pressing a button that activates an engine disconnect fault;
step two: producing engine-isolated acoustic and vibratory responses:
(1) the engine generates sound after being activated by the separation fault;
(2) generating vibration by a motion system of the airplane simulator;
step three: shift of center of gravity position;
step four: the engine loses thrust, the airplane deflects, the corresponding engine is closed by the background, and the state value is reset;
step five: the engine display disappears, and other systems report errors;
(1) the background closes the corresponding engine and stops sending signals to the display system;
(2) the hydraulic pressure, the fuel quantity, the power supply and the pneumatic system react to generate fault information;
step six: and (3) judging two conditions of fuel oil leakage:
(1) when fuel oil leaks, a pilot presses a fire-proof button or pulls a fire-proof handle, and then emergency operation treatment is carried out;
(2) the pilot directly carries out emergency operation treatment without fuel oil leakage;
step seven: when fuel leakage occurs, the fire-proof button is pressed out or the fire-proof handle is pulled up;
step eight: stopping fuel leakage;
step nine: pilot emergency operation treatment: the pilot carries out emergency operation treatment according to a quick check list, an engine fire alarm, a severe engine damage or a separation chapter;
step ten: and canceling the engine separation state and ending the scene.
Further, the engine red box display simulation method comprises the following steps:
the method comprises the following steps: the engine runs normally;
step two: activating an EGT overtemperature fault, wherein the EGT temperature changes along with the change of the throttle lever, and when the throttle lever is increased, the EGT is overrun;
step three: carrying out emergency operation treatment on the pilot, wherein the pilot carries out emergency operation treatment according to the quick inspection list;
step four: detecting whether the EGT is over-temperature or not, and continuously monitoring the EGT over-temperature zone bit by engine simulation software;
step five: recording an overtemperature state;
step six: and (3) shutting down the engine: the EGT of the engine is out of limit, and the double-engine is closed when the airplane is positioned on the bottom surface;
step seven: engine EGT red box display: activating an engine EGT red box display zone bit by using the EGT overtemperature state recorded in the step five, and enabling an engine display page to show an EGT red box;
step eight: pilot operation processing: finding the red box display of the engine EGT, and calling crew for maintenance;
step nine: restarting the engine, restarting the engine on the ground, and activating an EGT red box display flag bit of the engine to reset;
step ten: engine EGT red box disappeared:
(1) after the activation fault, the engine EGT is not out of limit, and the engine EGT red box is not displayed;
(2) after the EGT red box display flag bit is reset, the engine EGT red box display disappears.
Further, in the engine separation simulation method, the weight of the airplane is reduced and the center of gravity is shifted due to the separation of the engine in the third step, and the flying simulator adjusts the center of gravity of the airplane and changes the center of gravity entering the aerodynamic model.
Further, in the engine separation simulation method, the step five of stopping sending the signal to the display system comprises the step of enabling the engine indication to reflect the missing signal and enabling the display of the corresponding engine to return to zero or disappear.
The invention has the advantages and positive effects that:
1. by adding the engine separation fault simulation and the engine EGT red box display simulation, the problem that the existing flight simulator cannot meet the training requirement of a quick check list can be solved, the pilot is helped to be familiar with and know the problems of the engine separation fault and the fault displayed by the engine EGT red box, and the pilot is familiar with operation steps and a fault processing mode.
2. The real scene of the fault can be restored through the setting of the instructor, the fault training is carried out on the pilot, various judgment processes in the operation steps can be trained through the setting of the instructor, the emergency operation processing mode and the emergency operation processing flow of the pilot are trained, and the flight safety is improved.
Drawings
FIG. 1 is a diagram of a flight simulator simulation system of the present invention;
FIG. 2 is a diagram of the engine separation step of the present invention;
FIG. 3 is an engine disconnect flow diagram of the present invention;
FIG. 4 is a flow chart of the EGT red box display of the present invention.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, the method of simulated engine separation and EGT red box display on a flight simulator, the simulation system of the flight simulator includes flight guidance and control, aerodynamic models, a power system, a display system, and other systems, the power system includes an engine including an engine model, an engine interface, engine fault scenarios including engine separation, engine red box display, and other fault scenarios, engine sound, and engine vibration, and an APU.
As shown in fig. 2-3, the engine split simulation method:
the method comprises the following steps: activating engine disconnect, pressing a button that activates an engine disconnect fault;
step two: producing engine-isolated acoustic and vibratory responses:
(1) the engine generates sound after being activated by the separation fault;
(2) generating vibration by a motion system of the airplane simulator;
step three: the center of gravity is offset and engine separation results in reduced aircraft weight, with the center of gravity generally offset aft. Adjusting the center of gravity of the airplane to change the center of gravity entering the aerodynamic model so as to realize aerodynamic feeling change;
step four: the engine loses thrust, the airplane deflects, the background closes the corresponding engine and clears the state value to zero, so that the thrust of the corresponding engine disappears instantly, asymmetrical performance is caused due to the action of resistance and gravity, and the airplane deflects according to the current state;
step five: the engine display disappears, and other systems report errors;
(1) the background closes the corresponding engine and stops sending signals to the display system;
(2) the hydraulic pressure, the fuel quantity, the power supply and the pneumatic system react to generate fault information;
step six: and (3) judging two conditions of fuel oil leakage:
(1) when fuel oil leaks, a pilot presses a fire-proof button or pulls a fire-proof handle, and then emergency operation treatment is carried out;
(2) the pilot directly carries out emergency operation treatment without fuel oil leakage;
step seven: when fuel leakage occurs, the fire-proof button is pressed out or the fire-proof handle is pulled up;
step eight: stopping fuel leakage, and pressing a fire-proof button or pulling a fire-proof handle to cause fuel leakage;
step nine: pilot emergency operation treatment: the pilot carries out emergency operation treatment according to a quick check list, an engine fire alarm, a severe engine damage or a separation chapter;
step ten: and canceling the engine separation state and ending the scene.
As shown in fig. 4, the engine red box display simulation method:
the method comprises the following steps: the engine runs normally;
step two: the EGT overtemperature fault is activated, the EGT temperature changes along with the change of the throttle lever, when the throttle lever is increased, the EGT is overrun, and is simultaneously suitable for other EGT overtemperature conditions;
step three: carrying out emergency operation treatment on the pilot, wherein the pilot carries out emergency operation treatment according to the quick inspection list;
step four: detecting whether the EGT is over-temperature or not, and continuously monitoring the EGT over-temperature flag bit by engine simulation software;
step five: recording the EGT overtemperature state after the EGT of the engine is out of limit;
step six: and (3) shutting down the engine: the EGT of the engine is out of limit, and the double-engine is closed when the airplane is positioned on the bottom surface;
step seven: engine EGT red box display: activating an engine EGT red box display zone bit by using the EGT overtemperature state recorded in the step five, and enabling an engine display page to show an EGT red box;
step eight: pilot operation processing: finding the red box display of the engine EGT, and calling crew for maintenance;
step nine: restarting the engine, restarting the engine on the ground, and activating an EGT red box display flag bit of the engine to reset;
step ten: engine EGT red box disappeared:
(1) after the activation fault, the engine EGT is not out of limit, and the engine EGT red box is not displayed;
(2) after the EGT red box display flag bit is reset, the engine EGT red box display disappears.
And in the fifth step, the signals sent to the display system are stopped, wherein the signals comprise engine indication reflection missing signals and the display of the corresponding engine returns to zero or disappears.
In the third step, the separation of the engine leads to the reduction of the weight of the airplane and the shift of the gravity center, and the flight simulator adjusts the gravity center of the airplane and changes the gravity center entering the aerodynamic model.
The working process of the example is as follows: the corresponding fault simulation system is started through the flight simulator system, the fault is processed and solved according to the operation steps according to the fault prompt and the fault display, the pilot can be helped to be familiar with the fault state, the fault processing mode and the operation steps, and the pilot can operate timely to avoid tension or miss the optimal processing opportunity when the rare fault problem is faced.
While one embodiment of the present invention has been described in detail, the description is only a preferred embodiment of the present invention and should not be taken as limiting the scope of the invention. All equivalent changes and modifications made within the scope of the present invention shall fall within the scope of the present invention.
Claims (5)
1. A method for separating a simulation engine and displaying an EGT red box on a flight simulator is characterized by comprising the following steps: the simulation system of the flight simulator comprises flight guidance and control, an aerodynamic model, a power system, a display system and other systems, wherein the power system comprises an engine and an APU, the engine comprises an engine model, an engine interface, an engine fault scene, engine sound and engine vibration, and the engine fault scene comprises engine separation, engine red box display and other fault scenes.
2. The method of simulated engine separation and EGT red box display on a flight simulator as defined in claim 1, wherein: the simulation method of the engine separation comprises the following steps:
the method comprises the following steps: activating engine disconnect, pressing a button that activates an engine disconnect fault;
step two: producing engine-isolated acoustic and vibratory responses:
(1) the engine generates sound after being activated by the separation fault;
(2) generating vibration by a motion system of the airplane simulator;
step three: shift of center of gravity position;
step four: the engine loses thrust, the airplane deflects, the corresponding engine is closed by the background, and the state value is reset;
step five: the engine display disappears, and other systems report errors;
(1) the background closes the corresponding engine and stops sending signals to the display system;
(2) the hydraulic pressure, the fuel quantity, the power supply and the pneumatic system react to generate fault information;
step six: and (3) judging two conditions of fuel oil leakage:
(1) when fuel oil leaks, a pilot presses a fire-proof button or pulls a fire-proof handle, and then emergency operation treatment is carried out;
(2) the pilot directly carries out emergency operation treatment without fuel oil leakage;
step seven: when fuel leakage occurs, the fire-proof button is pressed out or the fire-proof handle is pulled up;
step eight: stopping fuel leakage;
step nine: pilot emergency operation treatment: the pilot carries out emergency operation treatment according to a quick check list, an engine fire alarm, a severe engine damage or a separation chapter;
step ten: and canceling the engine separation state and ending the scene.
3. The method of simulated engine separation and EGT red box display on a flight simulator as defined in claim 1, wherein: the engine red box display simulation method comprises the following steps:
the method comprises the following steps: the engine runs normally;
step two: activating an EGT overtemperature fault, wherein the EGT temperature changes along with the change of the throttle lever, and when the throttle lever is increased, the EGT is overrun;
step three: carrying out emergency operation treatment on the pilot, wherein the pilot carries out emergency operation treatment according to the quick inspection list;
step four: detecting whether the EGT is over-temperature or not, and continuously monitoring the EGT over-temperature flag bit by engine simulation software;
step five: recording an overtemperature state;
step six: and (3) shutting down the engine: the EGT of the engine is out of limit, and the double-engine is closed when the airplane is positioned on the bottom surface;
step seven: engine EGT red box display: activating an engine EGT red box display zone bit by using the EGT overtemperature state recorded in the step five, and enabling an engine display page to show an EGT red box;
step eight: pilot operation processing: finding the red box display of the engine EGT, and calling crew for maintenance;
step nine: restarting the engine, restarting the engine on the ground, and activating an EGT red box display flag bit of the engine to reset;
step ten: engine EGT red box disappeared:
(1) after the activation fault, the engine EGT is not out of limit, and the engine EGT red box is not displayed;
(2) after the EGT red box display flag bit is reset, the engine EGT red box display disappears.
4. The method of simulated engine separation and EGT red box display on a flight simulator as defined in claim 2, wherein: in the third step, the separation of the engine leads to the reduction of the weight of the airplane and the shift of the gravity center, and the flight simulator adjusts the gravity center of the airplane and changes the gravity center entering the aerodynamic model.
5. The method of simulated engine separation and EGT red box display on a flight simulator as defined in claim 2, wherein: and in the fifth step, the signals sent to the display system are stopped, wherein the signals comprise engine indication reflection missing signals and the display of the corresponding engine returns to zero or disappears.
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| Application Number | Priority Date | Filing Date | Title |
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| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
-
2022
- 2022-01-11 CN CN202210025406.XA patent/CN114360323B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020133322A1 (en) * | 2001-03-16 | 2002-09-19 | Williams Robert Arthur | Method of pilot training using simulated engine failure |
| US20030054324A1 (en) * | 2001-09-05 | 2003-03-20 | Fountain & Associates, Inc. | Training methods for aircraft simulator pilot |
| US20070164167A1 (en) * | 2006-01-13 | 2007-07-19 | Bachelder Edward N | Autorotation flight control system |
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| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
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