Landing gear analog stowage system

Abstract

The utility model relates to flight training equipment technical field discloses a kind of landing gear simulation retraction system, including control unit, signal acquisition module, landing control module, indicating lamp module and alarm module, landing control module, for output landing gear's retraction signal and put down signal;Indicating lamp module, for display landing gear retraction process in retraction state or put down state;Signal acquisition module, for collecting aircraft altitude signal and landing gear retraction signal;Control unit, for receiving aircraft altitude signal and landing gear retraction signal collected by signal acquisition module, and whether landing gear is correctly retracted is judged, when landing gear is not normally retracted, control unit exports alarm signal;Alarm module issues alarm according to alarm signal.The utility model patent solves the problem that landing gear retraction system cannot be systematically trained when fixed landing gear aircraft is used for training in existing flight training.

Description

Technical Field

[0001] This utility model relates to the field of flight training equipment technology, specifically to a landing gear simulation retraction system. Background Technology

[0002] Under the current civil aviation pilot training system, initial training typically uses aircraft equipped with small fixed landing gear as training aircraft. This means that pilots have no opportunity to practice landing gear retraction and extension during early routine training. This situation forces trainees to make a significant leap in experience when they later fly aircraft with retractable landing gear for advanced training. Especially after entering their professional careers, flight scenarios become increasingly complex and varied, with special flight situations occurring frequently. When faced with emergency landings, special airspace takeoffs and landings, or landings under complex weather conditions, pilots are highly susceptible to forgetting or delaying landing gear retraction and extension operations due to nervousness, especially since they lacked awareness of this technique during initial training. These errors not only pose a direct threat to flight safety but, in extreme cases, can trigger serious accidents, leading to major tragedies involving loss of life and property. Utility Model Content

[0003] The present invention aims to provide a solution to the problem that, in existing flight training programs using fixed landing gear systems, it is impossible to conduct systematic training on the landing gear retraction and extension system.

[0004] To solve the above problems, this utility model adopts the following technical solution: a landing gear simulation retraction system, including a control unit, a signal acquisition module, a landing control module, an indicator light module, and an alarm module.

[0005] The landing control module is used to output landing gear retraction and extension signals, which together constitute the landing gear retraction and extension signals.

[0006] The indicator light module is used to display the retracted or extended status of the landing gear during the retraction and extension process.

[0007] The signal acquisition module is used to acquire aircraft altitude signals and landing gear retraction / extension signals;

[0008] The control unit receives the aircraft altitude signal and landing gear retraction / extension signal from the signal acquisition module, and determines whether the landing gear is retracted or extended correctly based on the received aircraft altitude signal and landing gear retraction / extension signal. When the landing gear is not retracted or extended normally, the control unit outputs an alarm signal.

[0009] The alarm module is used to receive alarm signals from the control unit and issue alarms based on the alarm signals.

[0010] The principle and beneficial effects of this solution are as follows: During landing gear retraction and extension training, pilots need to control the retraction and extension of the landing gear according to the aircraft's altitude. For example, during the descent phase, as the aircraft gradually decreases in altitude, once it reaches a certain altitude (an alarm altitude can be set), the pilot needs to lower the landing gear according to the flight procedure to ensure a smooth landing. During takeoff, once the aircraft reaches a certain altitude and speed, the landing gear needs to be retracted. In this application, the landing gear retraction and extension signals are output by the landing gear control module to control the retraction or extension of the landing gear during takeoff and landing, serving as a training objective. During the pilot's operation, the landing gear control module outputs retraction and extension signals. After completing the corresponding control operation (e.g., retracting the landing gear), the indicator light module displays the current retracted state of the landing gear. Through the indicator light module's display status, the pilot can quickly and intuitively understand whether the landing gear retraction and extension operation has been successfully completed and whether the system is functioning normally.

[0011] In addition, this application also includes a signal acquisition module, which is used to acquire aircraft altitude signals and landing gear retraction / extension signals. When the aircraft altitude exceeds or falls below the alarm altitude, the landing gear needs to be retracted or extended accordingly. Therefore, during actual training, after the control unit receives the aircraft altitude signal and landing gear retraction / extension signal, it determines whether the landing gear is correctly retracted or extended based on the received signals. When the aircraft's flight altitude is above the alarm altitude, but the landing gear is still in the extended state, the control unit determines that the landing gear has not been retracted. At this time, the control unit generates an alarm signal, and the alarm module issues an alarm after receiving the signal to remind the pilot to retract the landing gear in time.

[0012] In this application, the landing gear retraction and extension process is simulated. By combining the collection of aircraft altitude signals and landing gear retraction and extension signals, it can accurately determine whether the landing gear is correctly retracted or extended, which is more consistent with the actual flight process and can provide more accurate training for pilots. Moreover, in this application, after the pilot outputs the landing gear retraction and extension signals using the landing gear control module, the indicator module can display the landing gear being in the retracted or extended state accordingly. After receiving the aircraft altitude signal and landing gear retraction and extension signal, the control unit can automatically determine whether the landing gear is correctly retracted or extended, and control the alarm module to sound an alarm when it fails to retract or extend normally. This allows the pilot to receive training on abnormal situations during the training process, so that they can skillfully deal with abnormal situations in subsequent actual flight, achieving a good training objective.

[0013] Preferably, as an improvement, the indicator module includes a stowage indicator and a put-down indicator.

[0014] In this solution, separate retraction and extension indicator lights are provided to display the retraction and extension of the landing gear, respectively. The display results are more accurate and the driver can clearly observe and judge.

[0015] Preferably, as an improvement, the lifting control module includes a single-pole double-throw switch. The single-pole double-throw switch includes a switching handle, two output terminals, and a fixed terminal. The fixed terminal is connected to the negative terminal of a DC power supply. The two output terminals of the single-pole double-throw switch are a lowering terminal and a retracting terminal, respectively. The retracting terminal is connected to one end of a retracting indicator light, and the other end of the retracting indicator light is connected to the positive terminal of the DC power supply. The lowering terminal is connected to both one end of a lowering indicator light and a control unit. The other end of the lowering indicator light is connected to the positive terminal of the DC power supply.

[0016] In this solution, by switching the handle to connect the moving end of the single-pole double-throw switch to the lowering or retracting end, the pilot can perform the operation of retracting or lowering the landing gear during flight training, which is consistent with the actual landing gear retraction and extension operation when flying an aircraft. When the fixed end is connected to the lowering or retracting end, the lowering indicator light or the retracting indicator light will illuminate, indicating that the pilot has completed the operation of retracting or lowering the landing gear. The pilot can accurately determine whether the corresponding control operation has been completed by observing whether the lowering or retracting indicator light is lit.

[0017] In addition, the lowering end of the single-pole double-throw switch in this solution is connected to both the lowering indicator light and the control unit. This means that when the pilot completes the "lowering" landing gear operation, not only will the lowering indicator light be energized and illuminated, but the control unit will also receive the landing gear lowering signal. In other cases, the control unit automatically determines that the landing gear is in the "retracted" state. The circuit is simple, clear, and accurate. The control unit can accurately receive and judge the landing gear retraction and extension signals, thereby accurately determining whether the landing gear is correctly retracted or extended in combination with the aircraft altitude signal.

[0018] Preferably, as an improvement, a first time relay is connected to the retractable indicator light, and a second time relay is connected to the drop-down indicator light. The delay time of both the first and second time relays is 5 to 10 seconds.

[0019] In this scheme, by setting a first time relay and a second time relay, when the driver operates the single-pole double-throw switch to complete the "retract" or "lower" operation of the landing gear, the retract or lower indicator light will light up after a delay of 5 to 10 seconds due to the presence of the first and second time relays. This closely matches the timing process of the landing gear retracting and lowering, more accurately demonstrating the landing gear retraction and extension control process, and achieving a more accurate training effect.

[0020] Preferably, as an improvement, the switching handle on the single-pole double-throw switch is connected to a contour handle.

[0021] In this solution, a contoured handle is fixedly connected to the switching handle of the single-pole double-throw switch. The contoured handle can be set to the control handle style of different aircraft models, so that the pilot's operation of the switching handle is more in line with the actual flight state, thus achieving a better training effect.

[0022] Preferably, as an improvement, it also includes an altitude signal receiving unit, which receives the aircraft altitude signal and transmits the aircraft altitude signal to the control unit.

[0023] In this solution, the altitude signal receiving unit receives the aircraft's altitude signal in real time and transmits it to the control unit. This allows the control unit to obtain the aircraft's altitude and determine whether the landing gear is correctly retracted or extended based on the altitude signal and the landing gear retraction / extension signal.

[0024] Preferably, as an improvement, a main flight display is connected between the altitude signal receiving unit and the control unit. The main flight display is used to display the aircraft altitude signal received by the altitude signal unit, which includes the altitude signal output by the barometric altimeter and / or radar altimeter.

[0025] In this solution, the main flight display shows the aircraft altitude signal, which includes the altitude signal output from the barometric altimeter and / or radar altimeter. In complex terrain and special weather conditions, when an abnormal alarm occurs, the flight altitude can be easily and quickly checked and judged, ensuring flight safety and accumulating driving experience for subsequent actual driving.

[0026] Of course, as a preferred method, the aircraft altitude signal can include only the altitude signal output by the barometric altimeter, eliminating the output signal of the radar altimeter, and directly using the altitude signal output by the aircraft's barometric altimeter as the input signal of the altitude signal receiving unit. The main flight display also only displays the altitude signal provided by the barometric altimeter, which is simpler and lower in cost.

[0027] Preferably, as an improvement, the control unit includes a controller and an XOR gate, one input of the XOR gate is connected to the main flight display, the other input of the XOR gate is connected to the down terminal of a single-pole double-throw switch, and the controller is connected to the output of the XOR gate.

[0028] In this scheme, the main flight display transmits the aircraft altitude signal to one input of the XOR gate, and the landing gear retraction and extension signal output by the landing control module is transmitted to the other input of the XOR gate. The two inputs of the XOR gate receive the aircraft altitude signal and the landing gear retraction and extension signal, perform logical judgment, and transmit the logical output of the judgment result to the controller. The controller controls whether the alarm module alarms according to the logical judgment result. The control is simple and the judgment is accurate.

[0029] Preferably, as an improvement, the controller includes an NE555 chip, pin 4 of the NE555 chip is connected to the output of an XOR gate, a first resistor is connected to pin 8 of the NE555 chip, the other end of the first resistor is connected to the positive terminal of a DC power supply, and pin 3 of the NE555 chip is connected to an alarm module.

[0030] In this solution, pin 4 of the NE555 chip is connected to the output of the XNOR gate to receive the logic output of the XNOR gate. At the same time, the alarm module is connected to pin 3 of the NE555 chip to facilitate the control of the alarm module to sound an alarm when the landing gear is not properly extended or retracted.

[0031] Preferably, as an improvement, the alarm module includes an alarm and a second resistor, one end of the second resistor is connected to pin 3 of the NE555 chip, and the alarm is connected between the other end of the second resistor and the negative terminal of the DC power supply.

[0032] In this scheme, the second resistor plays a protective role. When the landing gear fails to retract or extend correctly, the controller activates the alarm to alert the driver that the landing gear has not retracted or extended correctly. This allows the driver to contact and handle abnormal situations during training, thus completing the training more comprehensively. Attached Figure Description

[0033] Figure 1 This is a logic block diagram of Embodiment 1 of the present utility model.

[0034] Figure 2 This is a circuit diagram showing the connection between the landing control module and the indicator light module in Embodiment 1 of this utility model.

[0035] Figure 3 This is a circuit diagram showing the connection between the control unit and the alarm module in Embodiment 1 of this utility model.

[0036] Figure 4 This is a circuit diagram of Embodiment 1 of the present invention.

[0037] Figure 5 This is a circuit diagram showing the connection between the landing control module and the indicator light module in Embodiment 2 of this utility model.

[0038] Figure 6 This is a circuit diagram of Embodiment 2 of the present invention. Detailed Implementation

[0039] The following detailed description illustrates the specific implementation method:

[0040] The reference numerals in the accompanying drawings include: control unit 1, controller 101, signal acquisition module 2, take-off and landing control module 3, single-pole double-throw switch 301, indicator module 4, retract indicator 401, lower indicator 402, alarm module 5, red indicator 501, altitude signal receiving unit 6, and main flight display 7. Example

[0041] This embodiment is as shown in the attached figure. Figure 1 The diagram shows a landing gear retraction / extension simulation system, comprising a control unit 1, a signal acquisition module 2, a landing control module 3, an indicator light module 4, and an alarm module 5. The landing control module 3 outputs retraction and extension signals for the landing gear, which together constitute the landing gear retraction / extension signal. The indicator light module 4 displays the retraction or extension status of the landing gear during the retraction / extension process. The signal acquisition module 2 acquires the aircraft altitude signal and the landing gear retraction / extension signal. The control unit 1 receives the aircraft altitude signal and landing gear retraction / extension signal acquired by the signal acquisition module 2, and determines whether the landing gear is correctly retracted or extended based on the received signals. When the landing gear is not retracted or extended correctly, the control unit 1 outputs an alarm signal. The alarm module 5 receives the alarm signal from the control unit 1 and issues an alarm based on the alarm signal.

[0042] Specifically, in combination Figure 1 and Figure 2 The indicator module 4 includes a retractable indicator light 401 and a lowered indicator light 402. The lifting and lowering control module 3 includes a single-pole double-throw switch 301. The single-pole double-throw switch 301 includes a switching handle, two output terminals, and a fixed terminal. The fixed terminal is connected to the negative terminal of the DC power supply. The two output terminals of the single-pole double-throw switch 301 are the lowered terminal and the retracted terminal, respectively. The retracted terminal is connected to one end of the retractable indicator light 401, and the other end of the retractable indicator light 401 is connected to the positive terminal of the DC power supply. Figure 4 The lowering end is connected to one end of the lowering indicator light 402 and the control unit 1, while the other end of the lowering indicator light 402 is connected to the positive terminal of the DC power supply. To facilitate pilot operation during training, a contour handle is connected to the switching handle in this embodiment. The contour handle can be detachably connected to the switching handle using screws or other methods. The shape and style of the contour handle can be set differently for different aircraft models, with the contour handle being adapted to the corresponding aircraft model. This allows the pilot to approximate the actual situation of the corresponding aircraft model during training, resulting in more accurate and effective training.

[0043] Combination Figure 1 and Figure 4 This embodiment also includes an altitude signal receiving unit 6 and a main flight display (PFD). The main flight display 7 is connected between the altitude signal receiving unit 6 and the control unit 1. The altitude signal receiving unit 6 receives the aircraft altitude signal and transmits it to the main flight display 7. The aircraft altitude signal includes the altitude signal output from the barometric altimeter and / or radar altimeter. Specifically, in this embodiment, the altitude signal receiving unit 6 receives the altitude signal output from the radar altimeter, that is, it uses the radar altimeter to receive the aircraft altitude signal in real time during flight. The main flight display 7 receives the aircraft altitude signal and displays the aircraft altitude, while simultaneously transmitting the aircraft altitude signal to the control unit 1. By setting up the main flight display 7, the pilot can conveniently and quickly understand the aircraft's altitude during training, so as to perform different operational controls at different flight altitudes and achieve better training results. In other embodiments besides this one, to make control simpler and less costly, the altitude signal receiving unit 6 can only be used to receive the altitude signal output from the barometric altimeter, which can also accurately obtain the aircraft altitude signal; this will not be elaborated further here.

[0044] Combination Figure 1 and Figure 3 In this embodiment, the control unit 1 includes a controller 101 and an XNOR gate. The main flight display 7 transmits the aircraft altitude signal to one input of the XNOR gate, and the landing gear retraction signal output by the landing control module 3 is transmitted to the other input of the XNOR gate. In actual connection, one input of the XNOR gate is connected to the main flight display 7, and the other input of the XNOR gate is connected to the lower end of the single-pole double-throw switch 301. The controller 101 is connected to the output of the XNOR gate. In this embodiment, the controller 101 uses an NE555 chip. Pin 4 of the NE555 chip is connected to the output of the XNOR gate. A first resistor R7 is connected to pin 8 of the NE555 chip, and the other end of the first resistor R7 is connected to the positive terminal of the DC power supply. Pin 3 of the NE555 chip is connected to the alarm module 5. A voltage regulator circuit for stabilizing the voltage is connected between the XNOR gate and the NE555 chip. The voltage regulator circuit consists of a resistor R3 and a diode VD1. One end of the resistor R3 is connected to the XNOR gate, and the other end is connected to pin 8 of the NE555 chip. The positive terminal of the diode VD1 is connected to the XNOR gate, and the negative terminal is connected to the negative terminal of the DC power supply. In this embodiment, the alarm module 5 includes an alarm LED3 and a second resistor R4. One end of the second resistor R4 is connected to pin 3 of the NE555 chip, and the alarm LED3 is connected between the other end of the second resistor R4 and the negative terminal of the DC power supply. Specifically, the alarm is a red indicator light 501. In other embodiments besides this one, the alarm can be a buzzer or other alarm components, which will not be described here.

[0045] The specific implementation process is as follows:

[0046] This example illustrates a landing gear retraction training system used to train pilots on landing gear retraction operations. For instance, during training, it is required that the landing gear be retracted when the aircraft reaches a certain altitude (e.g., by setting an alarm altitude). In this training, the altitude signal receiving unit 6 first receives the aircraft's altitude signal. The main flight display 7 then displays the aircraft's altitude in real time. The pilot performs the corresponding operation based on the radar altitude displayed on the main flight display 7. For example, when the aircraft reaches an altitude of 150 meters (of course, the alarm altitude setting varies for different aircraft models and can be dynamically adjusted during actual training), the pilot needs to use the contour handle to push the switching handle of the single-pole double-throw switch 301 to connect it to the retraction end. The retraction indicator light 401 illuminates, indicating that... The landing gear retracts into position; simultaneously, one input of the XOR gate receives the aircraft altitude signal transmitted from the main flight display 7. Since the retraction terminal of the single-pole double-throw switch 301 is connected to the retraction indicator 401 at this time, no signal is input to the other input of the XOR gate (i.e., the landing gear retraction signal is 0). At this time, the XOR gate determines whether the landing gear has been correctly retracted based on the aircraft altitude signal and the landing gear retraction signal. When it determines that the landing gear has not been retracted correctly, it will output an alarm signal. After receiving the alarm signal, the controller 101 controls the alarm device to issue an alarm, prompting the pilot to correctly complete the landing gear retraction control.

[0047] When the XOR gate makes logical judgments based on the aircraft altitude signal and landing gear retraction / extension signal, the logic is as shown in Table 1:

[0048] Table 1 Logical judgments of the XNOR gate

[0049] Aircraft altitude signal Landing gear retraction signal Logical output 0 0 1 0 1 0 1 0 0 1 1 1

[0050] Aircraft altitude signal: 0: Output 0 when the altitude is above the alarm altitude; 1: Output 1 when the altitude is below the alarm altitude.

[0051] Landing gear retraction / extension signal: 0: Landing gear down; 1: Landing gear retracted.

[0052] The specific control logic is as follows:

[0053] 1. When the aircraft is flying above the alarm altitude and the landing gear is not retracted, the XOR gate outputs a high-level signal, triggering the NE555 chip to work, and the red indicator light 501 flashes to remind the pilot to retract the landing gear;

[0054] 2. When the aircraft is flying above the alarm altitude and the landing gear is retracted, the XOR gate outputs a low-level signal, the NE555 chip does not work, and the red indicator light 501 does not flash.

[0055] 3. When the aircraft is flying below the alarm altitude and the landing gear is not deployed, the XOR gate outputs a high-level signal, triggering the NE555 chip to work, and the red indicator light 501 flashes to remind the pilot to retract the landing gear.

[0056] 4. When the aircraft is flying below the alarm altitude and the landing gear is down, the XOR gate outputs a low-level signal, the NE555 chip does not work, and the red indicator light 501 does not flash.

[0057] Of course, in this embodiment, the alarm is a red indicator light 501. In other embodiments, the alarm can be set to multiple indicator lights of different colors, such as a combination of white and green lights. When the aircraft's altitude is above the alarm altitude and the landing gear is not retracted, the XOR gate outputs a high-level signal, triggering the NE555 chip to work. The white light flashes and the green light goes out, reminding the pilot to retract the landing gear. When the aircraft's altitude is above the alarm altitude and the landing gear is retracted, the XOR gate outputs a low-level signal, the NE555 chip does not work, the white light stays on, and the green light goes out. When the aircraft's altitude is below the alarm altitude and the landing gear is not deployed, the XOR gate outputs a high-level signal, triggering the NE555 chip to work. The green light flashes and the white light goes out, reminding the pilot to retract the landing gear. When the aircraft's altitude is below the alarm altitude and the landing gear is deployed, the XOR gate outputs a low-level signal, the NE555 chip does not work, the green light stays on, and the white light goes out. Alternatively, in practical applications, the alarm may use other combinations or display forms, which will not be listed here.

[0058] In this embodiment, after the driver completes the corresponding operation of landing gear retraction and extension during training, the indicator light module 4 will provide feedback on the control result, so that the driver can determine whether the corresponding operation control has been completed. When the driver fails to operate correctly, the alarm module 5 will automatically sound an alarm to remind the driver so that the driver can complete the training project accurately. During this period, the driver can contact and handle abnormal situations, which improves the authenticity and scientific nature of the training. Example

[0059] The difference between Example 2 and Example 1 is that: [The text abruptly ends here, likely due to an incomplete sentence or a formatting error.] Figure 5 and Figure 6In this embodiment, a first time relay is connected to the retraction indicator 401, and a second time relay is connected to the lowering indicator 402. The delay time of both the first and second time relays is 5 to 10 seconds. By setting the first and second time relays, when the driver manually pushes the switching handle to connect to the retraction end (or lowering end), the retraction indicator 401 (or lowering indicator 402) is delayed by 5 to 10 seconds (e.g., 8 seconds) under the delay effect of the first time relay. This delay time corresponds to the actual time required for the landing gear to retract after operation, more accurately displaying the driver's actual driving situation, further enhancing the realism of the training, and achieving better training results.

[0060] The above descriptions are merely embodiments of this utility model. Commonly known technical solutions and / or characteristics are not described in detail here. It should be noted that those skilled in the art can make various modifications and improvements without departing from the technical solution of this utility model. These modifications and improvements should also be considered within the scope of protection of this utility model, and will not affect the effectiveness of the implementation of this utility model or the practicality of the patent. The scope of protection claimed in this application should be determined by the content of its claims, and the specific embodiments described in the specification can be used to interpret the content of the claims.

Claims

1. A landing gear simulation retraction system, characterized in that: It includes a control unit, a signal acquisition module, a lifting and lowering control module, an indicator light module, and an alarm module. The landing control module is used to output landing gear retraction and extension signals, which together constitute the landing gear retraction and extension signals. The indicator light module is used to display the retracted or extended status of the landing gear during the retraction and extension process. The signal acquisition module is used to acquire aircraft altitude signals and landing gear retraction / extension signals; The control unit receives the aircraft altitude signal and landing gear retraction / extension signal from the signal acquisition module, and determines whether the landing gear is retracted or extended correctly based on the received aircraft altitude signal and landing gear retraction / extension signal. When the landing gear is not retracted or extended normally, the control unit outputs an alarm signal. The alarm module is used to receive alarm signals from the control unit and issue alarms based on the alarm signals.

2. The landing gear simulation retraction system according to claim 1, characterized in that: The indicator module includes a stowed indicator and a raised indicator.

3. The landing gear simulation retraction system according to claim 2, characterized in that: The lifting control module includes a single-pole double-throw switch, which includes a switching handle, two output terminals, and a fixed terminal. The fixed terminal is connected to the negative terminal of a DC power supply. The two output terminals of the single-pole double-throw switch are a lowering terminal and a retracting terminal, respectively. The retracting terminal is connected to one end of the retracting indicator light, and the other end of the retracting indicator light is connected to the positive terminal of the DC power supply. The lowering terminal is connected to both one end of the lowering indicator light and the control unit, and the other end of the lowering indicator light is connected to the positive terminal of the DC power supply.

4. The landing gear simulation retraction system according to claim 3, characterized in that: The retractable indicator light is connected to a first time relay, and the drop-down indicator light is connected to a second time relay. The delay time of both the first and second time relays is 5 to 10 seconds.

5. A landing gear simulation retraction system according to claim 3, characterized in that: The single-pole double-throw switch has a contoured handle connected to its switching handle.

6. A landing gear simulation retraction system according to claim 2, characterized in that: It also includes an altitude signal receiving unit, which is used to receive the aircraft altitude signal and transmit the aircraft altitude signal to the control unit.

7. A landing gear simulation retraction system according to claim 6, characterized in that: A main flight display is connected between the altitude signal receiving unit and the control unit. The main flight display is used to display the aircraft altitude signal received by the altitude signal receiving unit. The aircraft altitude signal includes the altitude signal output by the barometric altimeter and / or radar altimeter.

8. A landing gear simulation retraction system according to claim 7, characterized in that: The control unit includes a controller and an XOR gate. One input of the XOR gate is connected to the main flight display, and the other input of the XOR gate is connected to the down terminal of a single-pole double-throw switch. The controller is connected to the output of the XOR gate.

9. A landing gear simulation retraction system according to claim 8, characterized in that: The controller includes an NE555 chip. Pin 4 of the NE555 chip is connected to the output of an XOR gate. A first resistor is connected to pin 8 of the NE555 chip. The other end of the first resistor is connected to the positive terminal of a DC power supply. Pin 3 of the NE555 chip is connected to an alarm module.

10. A landing gear simulation retraction system according to claim 9, characterized in that: The alarm module includes an alarm and a second resistor. One end of the second resistor is connected to pin 3 of the NE555 chip, and the alarm is connected between the other end of the second resistor and the negative terminal of the DC power supply.

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