MCAS trim control simulation system

Abstract

The utility model relates to the technical field of aircraft balancing, and discloses an MCAS balancing control simulation system which comprises an AOA attack angle sensor module, a power supply module, an FCC module, a wireless remote controller module, an electric switch module, a stabilizer balancing motor control circuit, a stabilizer balancing motor and a horizontal stabilizer front edge. The power supply module is connected with the AOA attack angle sensor module, the FCC module and the stabilizer trim motor; the FCC module is in communication connection with the wireless remote controller module, and the FCC module is connected with the stabilizer trim motor through the switch module and the stabilizer trim motor control circuit; and the stabilizer balancing motor drives the front edge of the horizontal stabilizer to move upwards or downwards through a connecting rod. According to the utility model, the dynamic upward deflection process of the plane horizontal stabilizer according to MCAS control circuit instructions (including true instructions and false instructions) can be simulated.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft trimming, in particular to an MCAS trimming control simulation system. Background Art

[0002] At present, the retraining of 737MAX pilots is carried out in the aircraft simulation cockpit, and the pilots are not very clear about the working process of the MCAS (Maneuvering Characteristics Augmentation System) functional circuit. Without a dedicated MCAS functional circuit demonstration bench, aircraft maintenance personnel can only look at the aircraft circuit atlas, and the learning effect is poor. Most aircraft maintenance personnel have only a partial understanding of how the MCAS functional circuit automatically lowers the aircraft nose, and cannot intuitively see through actual operation training what control circuit is used to change the dangerous state of the aircraft when the MCAS functional circuit is abnormal. For example, when the aircraft is forced to lower its nose, the pilot cannot stop the aircraft nose from continuing to point down through the habitual pull rod action. If the pilot fails to take risk avoidance and remedial measures in time, a flight accident may occur. Therefore, when the 737MAX aircraft has a failure in the MCAS functional circuit-related components, if it is difficult to find the fault point in time, it will bury hidden dangers for flight safety. Therefore, it is urgent to conduct special training on the MCAS functional circuit for 737MAX pilots and aircraft maintenance personnel to better ensure the flight safety of 737MAX aircraft. Utility Model Content

[0003] The purpose of the utility model is to provide an MCAS trim control simulation system. On the MCAS trim control simulation system of the 737MAX aircraft, the horizontal stabilizer of the aircraft dynamically deflects upward according to the MCAS control circuit command (including true command and false command), and intuitively displays to the pilots and aircraft maintenance personnel the entire process from the issuance of the MCAS control circuit command to the various switches passed and then to the controlled movement of the horizontal stabilizer of the aircraft, so as to train the pilots and aircraft maintenance personnel in the ability to judge and troubleshoot the faults of the related components of the MCAS control circuit, so as to improve the ability to troubleshoot the faults of the related components of the MCAS control circuit, thereby improving the safety of flight.

[0004] In order to achieve the above-mentioned purpose, the utility model provides an MCAS trim control simulation system, including an AOA angle of attack sensor module, a power module, an FCC module, a wireless remote control module, an electric switch module, a stabilizer trim motor control circuit, a stabilizer trim motor motor and a horizontal stabilizer leading edge; the power module is connected to the AOA angle of attack sensor module, the FCC module and the stabilizer trim motor motor; the FCC module is communicatively connected to the wireless remote control module, and the FCC module is connected to the stabilizer trim motor motor through the electric switch module and the stabilizer trim motor control circuit; the stabilizer trim motor motor drives the horizontal stabilizer leading edge to move upward or downward through a connecting rod.

[0005] In some embodiments, the AOA angle of attack sensor module includes a first AOA angle of attack sensor and a second AOA angle of attack sensor, and a light emitting diode is arranged on the upper right of the first AOA angle of attack sensor and the second AOA angle of attack sensor, and the light emitting diode is used to simulate a pitch angle of the aircraft exceeding the MCAS threshold.

[0006] In some embodiments, the power supply of the power module is a low-voltage power supply, and the low-voltage power supply includes a 28V DC power supply and a 12V DC power supply. The 28V DC power supply is used to power the stabilizer trim motor, and the 12V DC power supply is used to power the AOA angle of attack sensor module and the FCC module; the power module includes three switches and three indicator lights.

[0007] In some embodiments, the FCC module includes two FCCs, and a NOSE UP switch and a NOSE DOWN switch are provided on a panel of the FCC for generating corresponding automatic trim instructions. The two FCCs are in the shape of a rectangular box, and an MCAS instruction light emitting diode is provided on the rectangular box.

[0008] In some embodiments, the switch module includes a first group of switches, a second group of switches, a third group of switches and an MCAS function relay (K3); the first group of switches includes a stabilizer main electrical trim switch and an analog stick switch, and the analog stick switch controls a first relay (K1) and a second relay (K2); the second group of switches is a stabilizer main electrical trim OVERRIDE switch; the third group of switches is a PRI and B / U stabilizer trim cut-off switch; the MCAS function relay (K3) is used to control the TRIM DOWN bypass circuit and the horizontal stabilizer high-speed trim.

[0009] In some embodiments, the stabilizer trim motor control circuit includes a first relay group, a second relay group, a third relay group, and a fourth relay group.

[0010] In some embodiments, an automatic trim limit switch S145 is provided above the front edge of the horizontal stabilizer, and an automatic trim limit switch S144 is provided below the front edge of the horizontal stabilizer.

[0011] The embodiment of the utility model provides an MCAS trim control simulation system, which has the following beneficial effects compared with the prior art:

[0012] On the MCAS trim control simulation system of the 737MAX aircraft, the aircraft's horizontal stabilizer dynamically deflects upward according to the MCAS control circuit instructions (including true instructions and false instructions), intuitively showing pilots and aircraft maintenance personnel the entire process from the issuance of the MCAS control circuit instructions to the various switches passed and then to the controlled movement of the aircraft's horizontal stabilizer. This trains pilots and aircraft maintenance personnel in their ability to judge and troubleshoot faults of MCAS control circuit-related components, thereby improving their ability to troubleshoot faults of MCAS control circuit-related components and thereby enhancing flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a block diagram of the components and connections of the MCAS trim control simulation system according to an embodiment of the utility model;

[0014] Figure 2 It is a structural schematic diagram of the MCAS trim control simulation system of an embodiment of the utility model. DETAILED DESCRIPTION

[0015] In order to make the above-mentioned purposes, features and advantages of the utility model more obvious and easy to understand, the specific implementation methods of the utility model are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the utility model. However, the utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the utility model, so the utility model is not limited by the specific embodiments disclosed below.

[0016] In the description of the present invention, it is necessary to understand that the terms "length", "width", "up", "down", etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0017] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present utility model, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0018] like Figure 1 As shown, an MCAS trim control simulation system of a preferred embodiment of the utility model includes an AOA angle of attack sensor module 1, a power module 2, an FCC module 3, a wireless remote control module 4, an electric switch module 5, a stabilizer trim motor control circuit 6, a stabilizer trim motor motor 7 and a horizontal stabilizer leading edge 8; the power module 2 is connected to the AOA angle of attack sensor module 1, the FCC module 3 and the stabilizer trim motor motor 7; the FCC module 3 is communicatively connected to the wireless remote control module 4, and the FCC module 3 is connected to the stabilizer trim motor motor 7 through the electric switch module 5 and the stabilizer trim motor control circuit 6; the stabilizer trim motor motor 7 drives the horizontal stabilizer leading edge 8 to move upward or downward through a connecting rod.

[0019] like Figure 2 As shown, Figure 2 It is a structural schematic diagram of the MCAS trim control simulation system of an embodiment of the utility model;

[0020] In a specific embodiment, the AOA angle of attack sensor module 1 includes a first AOA angle of attack sensor 11 and a second AOA angle of attack sensor 12. A light emitting diode 13 is arranged on the upper right of the first AOA angle of attack sensor 11 and the second AOA angle of attack sensor 12. The light emitting diode 13 is used to simulate the pitch angle of the aircraft exceeding the MCAS threshold. The light emitting diode 13 can be a red light emitting diode, such as a red LED.

[0021] In a specific embodiment, the power supply of the power module 2 is a low-voltage power supply, and the low-voltage power supply includes a 28V DC power supply and a 12V DC power supply. The 28V DC power supply is used to power the stabilizer trim motor, and the 12V DC power supply is used to power the AOA angle of attack sensor module 1 and the FCC module 3; the power module includes three switches 21 and three indicator lights 22.

[0022] In a specific embodiment, the FCC module 3 includes two FCCs (31), a NOSE UP switch 311 and a NOSE DOWN switch 312 are provided on a panel of the FCC (31) for generating corresponding automatic trim instructions, and the two FCCs (31) are in the shape of a rectangular box, and an MCAS instruction light emitting diode 314 is provided on the rectangular box.

[0023] It should be noted that, when the conditions are met, each FCC (31) can automatically generate a trim command. Moving the NOSE UP switch 311 or the NOSE DOWN switch 312 is equivalent to the FCC (31) generating a corresponding automatic trim command. At this time, the stabilizer trim motor 7 will drive the horizontal stabilizer front edge 8 to move upward or downward. The MCAS command LED 314 is a red LED. When the MCAS command LED 314 is on, it means that the aircraft has generated an MCAS command. At this time, the horizontal stabilizer front edge 8 automatically moves upward, and the aircraft moves in the direction of the nose down. In order to reproduce the real scene, the operator can use two wireless remote controllers A and B in the wireless remote controller module 4 to remotely control whether the MCAS command appears. For example, the wireless remote controller A controls one FCC to generate an MCAS command, and the wireless remote controller B controls another FCC to generate an MCAS command. When the wireless remote controller A is pressed, the MCAS command is generated, and when it is released, the MCAS command stops; when the wireless remote controller B is pressed once, the MCAS command is generated, and when it is released, the MCAS command does not stop, and when it is pressed again, the MCAS command stops.

[0024] In a specific embodiment, the switch module 5 includes a first group of switches 51, a second group of switches 52, a third group of switches 53 and an MCAS function relay 54 (K3); the first group of switches 51 includes a stabilizer main electrical trim switch 511 and a simulated joystick switch 512, and the simulated joystick switch 512 controls the first relay (K1) and the second relay (K2); the second group of switches 52 is a stabilizer main electrical trim OVERRIDE switch; the third group of switches 53 is a PRI and B / U stabilizer trim cut-off switch; the MCAS function relay 54 (K3) is used to control the TRIM DOWN bypass circuit and the horizontal stabilizer high-speed trim.

[0025] It should be noted that when the stabilizer main electrical trim switch 511 is moved to the left, the aircraft is simulated to lower its head and the front edge 8 of the horizontal stabilizer moves upward; when the stabilizer main electrical trim switch 511 is moved to the right, the aircraft is simulated to raise its head and the front edge 8 of the horizontal stabilizer moves downward; below the stabilizer main electrical trim switch 511 is the simulated joystick switch 512, and moving the simulated joystick switch 512 to the left is equivalent to pushing the joystick forward, and moving the simulated joystick switch 512 to the right is equivalent to pulling the joystick backward. The simulated joystick switch 512 controls two relays K1 and K2 to simulate the two sets of switches FWD and AFT under the aircraft joystick.

[0026] In a specific embodiment, the stabilizer trim motor control circuit 6 includes a first relay group 61 , a second relay group 62 , a third relay group 63 and a fourth relay group 64 .

[0027] It should be noted that the stabilizer trim motor control circuit 6 can complete the switching of automatic trim and main electric trim and the priority setting through the logical combination of relay contacts, and control the conversion of the upward and downward movement of the horizontal stabilizer front edge 8. The output of the stabilizer trim motor 7 drives the horizontal stabilizer front edge 8 to move upward or downward through the connecting rod 71 after gear reduction.

[0028] In a specific embodiment, an automatic trim limit switch S145 is provided above the front edge 8 of the horizontal stabilizer, and an automatic trim limit switch S144 is provided below the front edge 8 of the horizontal stabilizer.

[0029] It should be noted that in actual use, after the power is connected, the three switches of the power control box of the MCAS trim control simulation system are moved down, and the three red indicator lights are on, indicating that the power supply of the MCAS trim control simulation system is normal, and then the SPD TRIM+A / P ENGAGED switch 313 on the FCC panel is moved to the LED red position (high level), and then the NOSE UP switch 311 or the NOSE DOWN switch 312 is operated to move the front edge 8 of the horizontal stabilizer upward or downward; then the wireless remote control A is used to generate an MCAS command to move the front edge 8 of the horizontal stabilizer upward; the main electric trim switch of the stabilizer is used to return the front edge 8 of the horizontal stabilizer to the neutral position, and then the wireless remote control B is used to generate an MCAS command to move the front edge 8 of the horizontal stabilizer upward again.

[0030] In summary, an MCAS trim control simulation system provided by an embodiment of the utility model can dynamically deflect the aircraft's horizontal stabilizer upward according to MCAS control circuit instructions (including true instructions and false instructions) to intuitively show pilots and aircraft maintenance personnel the entire process from the issuance of MCAS control circuit instructions to the various switches passed and then to the controlled movement of the aircraft's horizontal stabilizer, thereby training pilots and aircraft maintenance personnel in the ability to judge and troubleshoot faults of MCAS control circuit-related components, thereby improving the ability to troubleshoot faults of MCAS control circuit-related components, thereby improving flight safety.

[0031] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principle of the present invention. These improvements and substitutions should also be regarded as the protection scope of the present invention.

Claims

1. An MCAS trim control simulation system, characterized in that: It includes an AOA angle of attack sensor module, a power module, an FCC module, a wireless remote control module, an electric switch module, a stabilizer trim motor control circuit, a stabilizer trim motor motor and a horizontal stabilizer front edge; the power module is connected to the AOA angle of attack sensor module, the FCC module and the stabilizer trim motor motor; the FCC module is communicatively connected to the wireless remote control module, and the FCC module is connected to the stabilizer trim motor motor through the electric switch module and the stabilizer trim motor control circuit; the stabilizer trim motor motor drives the horizontal stabilizer front edge to move upward or downward through a connecting rod.

2. The MCAS trim control simulation system as claimed in claim 1, characterized in that: The AOA angle of attack sensor module includes a first AOA angle of attack sensor and a second AOA angle of attack sensor. A light emitting diode is arranged on the upper right of the first AOA angle of attack sensor and the second AOA angle of attack sensor. The light emitting diode is used to simulate a pitch angle of the aircraft exceeding the MCAS threshold.

3. The MCAS trim control simulation system according to claim 1, characterized in that: The power supply of the power module is a low-voltage power supply, which includes a 28V DC power supply and a 12V DC power supply. The 28V DC power supply is used to power the stabilizer trim motor, and the 12V DC power supply is used to power the AOA angle of attack sensor module and the FCC module. The power module includes three switches and three indicator lights.

4. The MCAS trim control simulation system according to claim 1, characterized in that: The FCC module includes two FCCs, and a NOSE UP switch and a NOSE DOWN switch are provided on a panel of the FCC for generating corresponding automatic trim instructions. The two FCCs are in the shape of a rectangular box, and an MCAS instruction light emitting diode is provided on the rectangular box.

5. The MCAS trim control simulation system according to claim 1, characterized in that: The switch module includes a first group of switches, a second group of switches, a third group of switches and an MCAS function relay (K3); the first group of switches includes a stabilizer main electric trim switch and a simulated joystick switch, and the simulated joystick switch controls a first relay (K1) and a second relay (K2); The second group of switches are the stabilizer main electrical trim OVERRIDE switches; the third group of switches are the PRI and B / U stabilizer trim cut-off switches; the MCAS function relay (K3) is used to control the TRIM DOWN bypass circuit and the horizontal stabilizer high-speed trim.

6. The MCAS trim control simulation system according to claim 1, characterized in that: The stabilizer trim motor control circuit includes a first relay group, a second relay group, a third relay group and a fourth relay group.

7. The MCAS trim control simulation system according to claim 1, characterized in that: An automatic trim limit switch S145 is provided above the front edge of the horizontal stabilizer, and an automatic trim limit switch S144 is provided below the front edge of the horizontal stabilizer.

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