Horizontal stabilizer trim control system

Abstract

The present disclosure relates to a horizontal stabilizer trim control system and method. A horizontal stabilizer trim control method can include determining, by a flight control computer, a control command according to a flight control law based on flight data, transmitting, through a first bus, a master / standby channel control signal to a first channel computer of a first trim channel and a second channel computer of a second trim channel respectively to determine one of the first trim channel and the second trim channel as a master trim channel, transmitting, through the first bus, the control command to the master channel computer, transmitting, by the master channel computer, the control command to a master trim electronic controller through a second bus, transmitting, by the master trim electronic controller, the control command to a master control module, and acting, by the master control module, the control command on an actuator. The horizontal stabilizer trim control method according to the present disclosure can effectively prevent double simultaneous channel trim from occurring in various operating modes.

Description

Technical Field

[0001] This disclosure generally relates to the field of flight control, and more particularly to horizontal stabilizer trim control systems and methods. Background Technology

[0002] The horizontal stabilizer of an aircraft is the horizontal surface of the aircraft's tail section, generally classified into fixed and all-moving types. The function of the horizontal stabilizer is to provide the aircraft with appropriate static stability. Horizontal stabilizer trim is the process by which a trim system maintains the balance of the aircraft's horizontal stabilizer, thereby ensuring flight balance and safety. When an aircraft flies in a near-uniform straight line, it is often affected by various air currents or crosswinds, causing changes in its flight attitude. The horizontal stabilizer is trimmed accordingly to ensure flight safety. Before each takeoff, the downward angle of the horizontal stabilizer is appropriately adjusted based on the aircraft's takeoff weight and center of gravity position, determining whether the aircraft can take off safely.

[0003] Therefore, there is an urgent need for an efficient system and method for controlling the leveling of horizontally stable surfaces. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of such aspects. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify the key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as an introduction to the more detailed description that follows.

[0005] One embodiment of this disclosure provides a horizontal stabilizer trim control system. The horizontal stabilizer trim control system may include: a flight control computer; a first trim channel and a second trim channel coupled to the flight control computer, the first trim channel including a first channel computer, a first trim electronic controller, and a first control module, and the second trim channel including a second channel computer, a second trim electronic controller, and a second control module, wherein the flight control computer is configured to primarily control the first trim channel and the second trim channel; and an actuator coupled to the horizontal stabilizer, the first control module and the second control module being coupled to and controlling the actuator to control the horizontal stabilizer trim.

[0006] In one example, the horizontal stabilizer trim control system may further include a manual trim switch coupled between the first trim channel and the second trim channel.

[0007] In one example, either the first trim electronic controller or the second trim electronic controller includes: a bus signal processing module, a discrete signal processing module, a rate calculation module, a primary / backup decision module, a motor control module, and a brake control module.

[0008] In one example, both the first channel computer in the first trim channel and the second channel computer in the second trim channel are coupled to the flight control computer via a first bus; the first channel computer is coupled to the first trim electronic controller via a second bus, and the second channel computer is coupled to the second trim electronic controller via a second bus; and the first trim electronic controller is coupled to the second trim electronic controller via a third bus.

[0009] One embodiment of this disclosure provides a horizontal stabilizer trim control method. This horizontal stabilizer trim control method may include: a flight control computer determining control commands for the horizontal stabilizer based on flight data and a flight control law; the flight control computer transmitting channel selection signals via a first bus to a first channel computer of a first trim channel and a second channel computer of a second trim channel, respectively, to designate one of the first trim channel and the second trim channel as the primary trim channel and the other as the backup trim channel; the flight control computer transmitting control commands via the first bus to the primary channel computer of the primary trim channel; the primary channel computer transmitting the control commands via a second bus to the primary trim electronic controller of the primary trim channel; the primary trim electronic controller transmitting control commands to a primary control module; and the primary control module applying the control commands to actuators to control the horizontal stabilizer trim.

[0010] In one example, when the flight control computer fails, the horizontal stabilizer trim control method may further include: in response to a first trim electronic controller in a first trim channel and a second trim electronic controller in a second trim channel receiving a manual trim signal from a manual trim switch, the first trim electronic controller and the second trim electronic controller respectively transmitting the manual trim signal to the corresponding channel computer; the primary channel computer of the primary trim channel transmitting control commands to the primary trim electronic controller of the primary trim channel; and the primary trim electronic controller outputting control commands to the actuator to control the horizontal stabilizer.

[0011] In one example, when one of the channel computers in the first trim channel and the second trim channel fails, the horizontal stabilizer trim control method may further include: receiving control commands for the horizontal stabilizer from the flight control computer by the other non-failed channel computer in the first trim channel and the second trim channel; transmitting the control commands to the corresponding trim electronic controller by the other non-failed channel computer; and outputting control commands to the actuator by the corresponding trim electronic controller to control the horizontal stabilizer.

[0012] In one example, when both the first channel computer in the first trim channel and the second channel computer in the second trim channel fail, the horizontal stabilizer trim control method may further include: in response to the first trim electronic controller in the first trim channel and the second trim electronic controller in the second trim channel receiving a manual trim signal from a manual trim switch, a predetermined master trim electronic controller in the first trim electronic controller and the second trim electronic controller outputs a master control command to the actuator to control the horizontal stabilizer.

[0013] In one example, the horizontal stabilizer trim control method may further include: a backup trim electronic controller, predetermined from the first trim electronic controller and the second trim electronic controller, outputting a backup control command to the actuator, wherein the backup control command includes releasing the corresponding brake.

[0014] In one example, the first and second trim electronic controllers interact via a third bus to prevent simultaneous trimming of both channels.

[0015] Compared with the prior art, the horizontal stabilizer control system and method according to this disclosure can effectively prevent simultaneous trimming of dual channels in various operating modes, while reducing the number of discrete signals to avoid the heavy weight caused by long-distance logic level transmission and signal distortion caused by impedance non-uniformity, thus ensuring efficient trimming of the horizontal stabilizer and greatly improving the flight safety of the aircraft.

[0016] This disclosure is provided to introduce concepts in a simplified form, which will be further described in the detailed description below. This disclosure is not intended to identify key or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter. Other aspects, features, and / or advantages of the embodiments will be set forth in part in the description which follows, and will be apparent in part from the description, or may be learned by practice of this disclosure. Attached Figure Description

[0017] To gain a more detailed understanding of the features described above in this disclosure, reference can be made to a more specific description of the above-briefly summarized aspects, some of which are illustrated in the accompanying drawings. However, it should be noted that the drawings illustrate only certain typical aspects of this disclosure and should not be considered as limiting its scope, as other equivalent aspects are permissible in this description. In the drawings:

[0018] Figure 1 A diagram of the existing architecture of a horizontal stabilizer trim system is shown.

[0019] Figure 2 An architectural diagram of a horizontal stabilizer trim system according to an embodiment of the present disclosure is shown.

[0020] Figure 3 A flowchart of a horizontal stabilizer balancing method according to an embodiment of the present disclosure is shown.

[0021] Figures 4A-4B A logic diagram of a trim electronic controller according to an embodiment of the present disclosure is shown.

[0022] Figures 5A-5D A signal flow diagram for a horizontal stabilizer trimming system according to an embodiment of the present disclosure is shown. Detailed Implementation

[0023] The specific embodiments described below with reference to the accompanying drawings are intended as descriptions of various configurations and are not intended to represent only the configurations in which the concepts described herein can be practiced. These specific embodiments include detailed descriptions to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts can be practiced without these detailed descriptions.

[0024] Based on this teaching, those skilled in the art will appreciate that the scope of this disclosure is intended to cover any aspect of this disclosure, whether implemented independently of or in combination with any other aspect of this disclosure. For example, any number of the aspects described can be used to implement an apparatus or method of practice. Furthermore, the scope of this disclosure is intended to cover such apparatus or methods practiced using other structures, functionalities, or structures and functionalities that complement or differ from the various aspects of this disclosure described.

[0025] While specific aspects are described herein, numerous variations and substitutions of these aspects fall within the scope of this disclosure. Although some benefits and advantages of preferred aspects have been mentioned, the scope of this disclosure is not intended to be limited to a particular benefit, use, or objective. The detailed description and accompanying drawings are merely illustrative and not limiting of this disclosure, the scope of which is defined by the appended claims and their equivalents.

[0026] The function of the horizontal stabilizer is to provide the aircraft with appropriate static stability. Horizontal stabilizer trim is achieved by maintaining the balance of the aircraft's horizontal stabilizer through a trim system, thereby ensuring aircraft balance and flight safety. The horizontal stabilizer trim system commonly used in current flight control systems includes a flight control computer 105, an actuator controller 110, a dual-channel motor controller 125, and a horizontal stabilizer trim actuator 130, where the dual-channel motor controller 125 employs a dual-channel primary / standby operating mode. Figure 1 A diagram of the existing architecture of the horizontal stabilizer trim system 100 is shown.

[0027] like Figure 1As shown, the flight control computer 105 is connected to three actuator controllers 110A, 110B, and 110C via a bus. In some cases, actuator controllers 110A and 110C are connected to the first channel CH1 and the second channel CH2 of the dual-channel motor controller 125, respectively, to communicate bus signals and discrete signals to each other. For example, the discrete signals include motor control discrete signals and brake control discrete signals. In some cases, actuator controller 110B is connected to the first channel CH1 of the dual-channel motor controller 125. For example, actuator controller 110B may transmit a switch suppression signal to the first channel CH1 of the dual-channel motor controller 125.

[0028] In some configurations, the horizontal stabilizer trim system further includes a manual trim switch 115 and a trim cut-off switch 120. Furthermore, the manual trim switch 115 and trim cut-off switch 120 are respectively connected to a first channel CH1 and a second channel CH2 in the dual-channel motor controller 125 to transmit manual trim signals and trim cut-off signals to the first channel CH1 and the second channel CH2. The dual-channel motor controller 125 can execute automatic trim commands transmitted by the flight control computer 105 / actuator controller 110 via bus signals and discrete signals, and can also execute manual trim signals from the manual trim switch 115. The trim cut-off switch 120 is provided in the cockpit for the pilot to cut off horizontal stabilizer motion, and is given first priority. In either mode, when the pilot cuts off horizontal stabilizer motion, the dual-channel motor controller 125 stops motor control and stops supplying power to the actuators, causing the actuators to lock.

[0029] When the flight control system is in normal mode (in the air), the flight control computer 105 generates automatic trim commands based on the flight control law and transmits the automatic trim commands to actuator controllers 110A and 110B via the bus. Actuator controllers 110A and 110B then transmit the automatic trim commands to the dual-channel motor controller 125 via the bus.

[0030] When the flight control system is in normal mode (on the ground) or auxiliary mode, the dual-channel motor controller 125 receives a manual trim signal from the manual trim switch 115 and transmits the manual trim signal to the actuator controller 110 / flight control computer 105 via the bus. The actuator controller 110 / flight control computer 105 calculates the trim rate based on the manual trim signal and transmits the trim rate and control discrete signals to the dual-channel motor controller 125.

[0031] When the flight control system is in direct mode (e.g., when the flight control computer 105 fails, or when actuator controllers 110A and 110C fail), the dual-channel motor controller 125 receives a manual trim signal and transmits the trim signal to actuator controllers 110A and 110C. Actuator controllers 110A and 110C calculate the trim rate based on the manual trim signal and transmit the trim rate to the first channel CH1 of the dual-channel motor controller 125 via bus signals and control discrete signals.

[0032] When the flight control system is in standby trim mode (e.g., the flight control computer 105 fails, and both actuator controllers 110A and 110C fail), the dual-channel motor controller 125 directly responds to the manual trim signal from the manual trim switch and controls the horizontal stabilizer trim actuator 130 to operate in low-speed mode.

[0033] The horizontal stabilizer trim system 100 described above presents the following risks. For example, when the actuator controller 110C fails, the first channel CH1 in the dual-channel motor controller 125 will directly respond to the manual trim signal from the manual trim switch. However, the first channel CH2 in the dual-channel motor controller 125 still receives automatic trim commands from the actuator controller 110C, posing a risk of simultaneous trimming by both channels. Furthermore, the horizontal stabilizer trim system 100 described above uses multiple discrete signals as enable logic conditions and dual trim suppression for the actuator controllers 110A, 110B, and 110C. However, long-distance logic level transmission, while introducing significant mass to the aircraft, may also lead to signal distortion due to impedance inhomogeneity.

[0034] To address one or more of the above-mentioned technical problems, this disclosure provides a horizontal stabilizer trimming control system. The details will be described below with reference to the accompanying drawings.

[0035] Figure 2A schematic diagram of a horizontal stabilizer trim system 200 according to an embodiment of the present disclosure is shown. In this embodiment, the horizontal stabilizer trim control system 200 may include: a flight control computer 205; a first trim channel and a second trim channel coupled to the flight control computer 205. In some cases, the flight control computer 205 may be configured to master the first trim channel and the second trim channel. The first trim channel includes a first channel computer 210A, a first horizontal stabilizer trim electronic controller 215A (hereinafter referred to as the first trim electronic controller 215A), and a first control module 220A. The second trim channel includes a second channel computer 210B, a second horizontal stabilizer trim electronic controller 215A (hereinafter referred to as the second trim electronic controller 215A), and a second control module 220B. The horizontal stabilizer trim control system 200 may further include an actuator 225 coupled to the horizontal stabilizer. In some cases, the first control module 220A and the second control module 220B can be connected to the actuator 225 and control the actuator 225 to control the balancing of the horizontal stabilizer.

[0036] In one example, the horizontal stabilizer trim control system 200 may further include a manual trim switch 230 coupled between the first trim channel and the second trim channel. In one example, either the first trim electronic controller 215A or the second trim electronic controller 215B may include a bus signal processing module, a discrete signal processing module, a rate calculation module, a primary / standby decision module, a motor control module, and a brake control module. In one example, both the first channel computer 210A in the first trim channel and the second channel computer 210B in the second trim channel may be coupled to the flight control computer 205 via a first bus 235. In one example, the first channel computer may be coupled to the first trim electronic controller 215A via a second bus 240, and the second channel computer may be coupled to the second trim electronic controller 215B via a second bus 240. In one example, the first trim electronic controller 215A is coupled to the second trim electronic controller 215B via a third bus 245.

[0037] In some scenarios, the flight control computer 205 can receive flight data (e.g., atmospheric data, inertial navigation data, angle of attack data, etc. during flight) and determine automatic trim commands for the horizontal stabilizer based on the flight control law. Subsequently, the flight control computer 205 transmits the automatic trim commands to the first channel computer 210A and the second channel computer 210B via the first bus 235. Furthermore, the first channel computer 210A and the second channel computer 210B receive the automatic trim commands and transmit them via the second bus 240 to the corresponding first horizontal stabilizer trim controller 215A and the second trim electronic controller 215B, respectively. Additionally, the first channel computer 210A and the second channel computer 210B also transmit channel selection signals (e.g., via hardwire) to the corresponding first horizontal stabilizer trim controller 215A and the second trim electronic controller 215B, respectively. In some scenarios, the flight control computer 205 determines the primary / backup channel based on the parity of the date and transmits the primary / backup channel information to the corresponding channel computer via the first bus 235. The channel computer can then convert the primary / backup channel information into channel selection signals. The first horizontal stabilizer trim controller 215A and the second trim electronic controller 215B form a dual-channel controller operating in primary / backup mode. Both channels of the dual-channel controller receive bus signals (e.g., automatic trimming commands) and discrete signals (e.g., communication selection signals) from the corresponding first channel computer 210A and second channel computer 210B via the second bus 240 to form control commands for controlling actuator operation. Furthermore, the first horizontal stabilizer trim controller 215A and the second trim electronic controller 215B also receive manual trimming signals (e.g., via hardwired connections) from the manual trim switch 230 to form control commands for controlling actuator 225 operation. The first horizontal stabilizer trim controller 215A and the second trim electronic controller 215B exchange information via the third bus 250 to achieve primary / backup determination in manual trim switch trimming mode, effectively preventing simultaneous trimming of both channels. Simultaneous balancing of the dual channels will cause irreversible damage to the horizontal stabilizer balancing controller and actuator 225.

[0038] In one example, the actuator is an electromechanical actuator, consisting of dual motors, dual brakes, ball screws, and position sensors, which converts the rotational motion of the motors into the deflection motion of the control surfaces. In another example, the manual trim switch is located in the cockpit, providing the pilot with the input to manually trim the horizontal stabilizer. In some applications, the pilot can directly control the movement of the horizontal stabilizer by operating (e.g., pressing or rotating) the manual trim switch.

[0039] Figure 3A flowchart of a horizontal stabilizer trimming method 300 according to an embodiment of the present disclosure is shown. According to this embodiment, the horizontal stabilizer trimming control method 300 may include the following steps.

[0040] At 305, the flight control computer 205 determines control commands for the horizontal stabilizer based on the flight control law according to the flight data. For example, the flight control computer 205 may receive flight data (e.g., atmospheric data, inertial navigation data, angle of attack data, etc.) and then determine control commands for the horizontal stabilizer (e.g., the speed of motion of the horizontal stabilizer) in the air according to the flight control law.

[0041] At 310, the flight control computer 205 transmits channel strobe signals (e.g., channel activation signals) via the first bus 235 to the first channel computer 210A of the first trim channel and the second channel computer 210B of the second trim channel, respectively, to designate one of the first trim channel and the second trim channel as the primary trim channel and the other as the backup trim channel. In some alternative scenarios, the flight control computer 205 determines the primary / backup channel based on the parity of the date and transmits the primary / backup channel information to the corresponding channel computer via the first bus 235. The channel computer can then convert the primary / backup channel information into a channel strobe signal. For example, in the following description, the first trim channel is described as the primary trim channel and the second trim channel as the backup trim channel.

[0042] At 315, the flight control computer 205 transmits control commands to the primary channel computer of the primary trim channel via the first bus. For example, the flight control computer 205 can transmit control command 210A to the first channel computer via the first bus. In some cases, the flight control computer 205 does not transmit control command 210B to the second channel computer.

[0043] At 320, the primary channel computer transmits control commands to the primary trim electronic controller of the primary trim channel via the second bus. For example, the first channel computer 210A transmits control commands to the first trim electronic controller 215A of the first trim channel via the second bus 240. In some cases, the second channel computer 210A does not transmit control commands to the second trim electronic controller 215B.

[0044] At 325, the primary trim electronic controller transmits control commands to the primary control module. For example, the first trim electronic controller 215A transmits control commands to the first control module 220A. In some cases, the second trim electronic controller 215A does not transmit control commands to the second control module 220A.

[0045] At 330, the main control module applies control commands to the actuator to control the horizontal stabilizer trimming. For example, the first control module 220A applies control commands to the actuator 225 to control the horizontal stabilizer trimming. In some cases, either the first control module 220A or the second control module 220B may each include a motor control module and a brake control module, as described above. Thus, the control commands may include motor motion control commands and brake release control commands. Preferably, the control commands may further include motor motion rate control commands. The signal flow diagram of the above-described horizontal stabilizer trimming control method 300 in normal mode is shown below. Figure 5A To describe it. In normal mode, it does not respond to manual trim signals from the manual trim switch.

[0046] In one example, when the flight control computer 205 fails, the horizontal stabilizer trim control method 300 may further include: in response to the first trim electronic controller 215A and the second trim electronic controller 215B receiving a manual trim signal from the manual trim switch 230, the first trim electronic controller 215A and the second trim electronic controller 215B respectively transmit the manual trim signal to the corresponding channel computer; the primary channel computer of the primary trim channel transmits a control command to the primary trim electronic controller of the primary trim channel; and the primary trim electronic controller outputs a control command to the actuator to control the horizontal stabilizer. For example, the first channel computer 210A transmits a control command to the first trim electronic controller 215A, and the first trim electronic controller 215A outputs a control command to the actuator 225 to control the horizontal stabilizer. When the flight control computer fails, the flight control laws stored in the flight control computer 205 also fail. At this time, the horizontal stabilizer trim control system will be in degraded mode, and the horizontal stabilizer motion will be manually trimmed. The signal flow diagram of the above-mentioned horizontal stabilizer trim control method 300 in degraded mode is shown below. Figure 5BTo describe this, for example, the pilot continuously presses the manual trim switch in the cockpit in any direction (up or down). The manual trim signal from the manual trim switch is transmitted to the first trim electronic controller 215A and the second trim electronic controller 215B, respectively. The first trim electronic controller 215A and the second trim electronic controller 215B then transmit the manual trim signal to the corresponding channel computer via the second bus 240. In some cases, the channel computer calculates control commands (e.g., trim rate) based on the manual trim signal according to the master / slave relationship stored in normal mode. For example, the first channel computer transmits the control command to the first trim electronic controller 215A via the second bus and transmits the channel strobe signal to the first trim electronic controller 215A via hardwired transmission. In some cases, the second channel computer does not transmit control commands or channel strobe signals. The first trim electronic controller 215A processes the received control commands and channel strobe signals, as illustrated in the schematic diagram of the specific processing logic. Figure 4A As shown, the control command will then be applied to the actuator to control the leveling of the horizontal stabilizer. Figure 4AAs shown, the second bus signals transmitted via the second bus 240 may include motor motion control commands (optionally including motor motion rate commands), brake release control commands, and the validity of the second bus 240 in this channel. For example, the validity of the second bus 240 in this channel (e.g., the first channel) is transmitted to an adjacent channel (e.g., the second channel) via a third bus. Similarly, the validity of the second bus 240 in the second channel is transmitted to the first channel (e.g., the first trim electronic controller 215A) via a third bus. The third bus signals transmitted via the third bus 245 may include the validity of the third bus, the validity of the second bus 240 in an adjacent channel, etc. Discrete signals transmitted via hardwire may include: manual trim signals and channel selection signals. The primary / standby trim determination module may determine whether this channel is the primary trim channel or the standby trim channel based on the validity of the second bus 240 in this channel, the validity of the third bus, and the validity of the second bus 240 in this channel. In response to determining that this channel is the primary trim channel, the rate calculation module calculates the trim rate and then transmits the control commands and trim rate to the motor control module and the control commands to the brake release module. According to the bus protocol, the validity of the bus is determined by checking the following: Preamble Correctness: The purpose of the preamble is to establish a stable reception process. The receiver establishes a corresponding decoding state by recognizing a valid preamble. When no information is received or an error is detected, the receiver defaults to searching for a valid preamble. Once the beginning of a message is recognized, the reception result is either valid or invalid. Failure to recognize a preamble is defined as "No Message"; Bus Label Verification: The bus feedback command packet received at the bus port is verified against the expected label to ensure it matches the expected label; Bus CRC Verification: The transmitter transmits the calculated CRC to the receiver via the bus. The receiver also performs polynomial calculations to ensure the correctness and integrity of data transmission. Incorrectness in any of these three items will render the bus invalid.

[0047] In one example, when one of the channel computers in the first trim channel and the second trim channel fails, the horizontal stabilizer trim control method may further include: receiving control commands for the horizontal stabilizer from the flight control computer by the other non-failed channel computer in the first trim channel and the second trim channel; transmitting the control commands to the corresponding trim electronic controller by the other non-failed channel computer; and outputting control commands to the actuators by the corresponding trim electronic controller to control the horizontal stabilizer. When a single channel computer fails, the horizontal stabilizer trim control system will be in degraded mode, and the horizontal stabilizer movement will still be an automatic trim command. At this time, both manual trim signals and automatic trim commands exist, which may result in dual-channel trim. To prevent dual-channel trim when a single channel computer fails, the validity of the current bus and the validity of adjacent channels can be determined. In some cases, when a single channel computer fails, the trim electronic controller corresponding to the failed channel computer does not respond to manual trim signals. The horizontal stabilizer motion is then executed by the trim electronic controller corresponding to the working channel computer, following the automatic trim commands received from the flight control computer. The signal flow diagram of the aforementioned horizontal stabilizer trim control method 300 in degraded mode is shown below. Figure 5C To describe this, for example, the pilot continuously presses the manual trim switch in the cockpit in any direction (up or down). The manual trim signal from the manual trim switch is transmitted to the first trim electronic controller 215A and the second trim electronic controller 215B, respectively. The first trim electronic controller 215A and the second trim electronic controller 215B then transmit the manual trim signal to the corresponding channel computer via the second bus 240. When the channel computer of this channel (e.g., the second trim channel) fails (the second bus 240 fails), the second bus 240 of the adjacent channel becomes active. The first channel computer receives control commands for the horizontal stabilizer from the flight control computer; the first channel computer transmits the control commands to the first trim electronic controller; and the first trim electronic controller outputs control commands to the actuators to control the horizontal stabilizer. At this time, the trim electronic controller corresponding to the normal channel computer trims the horizontal stabilizer according to the automatic trim command. The specific processing logic diagram is shown above. Figure 4A As shown, it will not be elaborated further here.

[0048] In one example, when both the first channel computer in the first trim channel and the second channel computer in the second trim channel fail, the horizontal stabilizer trim control method may further include: in response to the first trim electronic controller in the first trim channel and the second trim electronic controller in the second trim channel receiving a manual trim signal from a manual trim switch, a predetermined master trim electronic controller in the first and second trim electronic controllers outputs a main control command to the actuator to control the horizontal stabilizer. In this example, the horizontal stabilizer trim control method may further include: a predetermined backup trim electronic controller in the first and second trim electronic controllers outputs a backup control command to the actuator, wherein the backup control command includes releasing the corresponding brake. When both channel computers fail, the horizontal stabilizer trim control system will be in backup trim mode, and the horizontal stabilizer will be manually trimmed. The signal flow diagram of the above-described horizontal stabilizer trim control method 300 in backup trim mode is shown below. Figure 5D To describe it. For example, if the pilot continuously presses the manual trim switch in the cockpit in any direction (up or down), the manual trim signal from the manual trim switch is transmitted via hardwire to the first trim electronic controller 215A and the second trim electronic controller 215B respectively. In some cases, both channels are in the released state in the standby trim mode. In the backup operating mode, both channels of the trim electronic controller receive the manual trim signal, which will inevitably result in dual-channel trim. Since there is no valid second bus 240 in the standby trim mode, the specific processing logic of the preset standby trim electronic controller is as follows: Figure 4B As shown. With Figure 4A Compared to the specific processing logic shown in the degradation mode, in Figure 4B In the specific processing logic shown, the backup trim electronic controller (e.g., the second trim electronic controller) does not respond to manual trim signals, effectively preventing dual-channel trimming in backup mode. In some cases, the non-backup trim electronic controller directly executes the manual trim signal to control the motor at low speed. In other cases, the dual channels of the trim electronic controller continue to transmit the second bus signal to the channel computer.

[0049] In one example, the first and second trim electronic controllers interact via a third bus to prevent simultaneous trimming of both channels. For instance, the first and second trim electronic controllers interact via the third bus to determine the validity of each other's second bus 240 to prevent simultaneous trimming of both channels.

[0050] Compared to conventional horizontal stabilizer trim systems, the horizontal stabilizer trim system according to this disclosure, in normal mode, uses trim electronic controllers with two trim channels to control single-channel actuators in a primary / backup relationship based on bus signals and discrete signals from the flight control computer and / or channel computers, preventing dual-channel trim. In different failure modes, a preset backup trim judgment module in the trim electronic controller effectively prevents dual-channel trim. For example, when a single channel computer fails, the trim electronic controller corresponding to the normal channel computer performs horizontal stabilizer trim according to automatic trim instructions. Alternatively, when both channel computers fail, manual trim is performed through a preset backup trim judgment module in the trim electronic controller, effectively preventing dual-channel trim. Furthermore, the horizontal stabilizer trim system according to this disclosure reduces the number of discrete signals, uses a single channel selection signal for primary / backup allocation, and increases the bus between the first and second trim electronic controllers to prevent simultaneous dual trim.

[0051] Those skilled in the art will clearly understand from the above embodiments that this disclosure can be implemented by software with the necessary hardware, or by hardware, firmware, etc. Based on this understanding, embodiments of this disclosure can be implemented in part in software form. The computer software can be stored on a readable storage medium, such as a floppy disk, hard disk, optical disk, or computer flash memory. The computer software includes a series of instructions to cause a computer (e.g., a personal computer, service station, or network terminal) to perform methods or portions thereof according to various embodiments of this disclosure.

[0052] The word “exemplary” is used herein to mean “serving as an example, embodiment, or illustration.” Any aspect described herein as “exemplary” is not necessarily to be construed as superior to or better than the others.

[0053] The preceding description is provided to enable any person skilled in the art to practice the various aspects described herein. Various modifications to these aspects will readily be understood by those skilled in the art, and the universal principles defined herein may be applied to other aspects. Therefore, the claims are not intended to be limited to the aspects shown herein, but are to be granted the full scope consistent with the language of the claims, wherein references to the singular form of an element, unless specifically stated otherwise, are not intended to mean “one and only one,” but rather “one or more.” Unless specifically stated otherwise, the term “some” refers to one or more. All structural and functional equivalents of the elements of the various aspects described throughout this disclosure, whether now or hereafter known to a person skilled in the art, are expressly incorporated herein by reference and are intended to be covered by the claims.

Claims

1. A method for controlling the balancing of a horizontal stabilizer, comprising: The flight control computer determines the control commands for the horizontal stabilizer based on the flight control law and flight data. The flight control computer transmits channel selection signals to the first channel computer of the first trim channel and the second channel computer of the second trim channel, respectively, so as to determine one of the first trim channel and the second trim channel as the primary trim channel and the other as the backup trim channel. The flight control computer transmits the control commands to the primary channel computer of the primary trim channel via the first bus; The main channel computer transmits the control commands to the main balance electronic controller of the main balance channel via the second bus; The main balance electronic controller transmits the control commands to the main control module; as well as The main control module applies the control commands to the actuator to control the balancing of the horizontal stabilizer.

2. The horizontal stabilizer balancing control method as described in claim 1, characterized in that, When the flight control computer fails, the horizontal stabilizer trim control method further includes: In response to the first trimming electronic controller in the first trimming channel and the second trimming electronic controller in the second trimming channel receiving a manual trimming signal from the manual trimming switch, the first trimming electronic controller and the second trimming electronic controller respectively transmit the manual trimming signal to the corresponding channel computer. The main channel computer of the main trim channel transmits the control commands to the main trim electronic controller of the main trim channel; and The main balance electronic controller outputs the control command to the actuator to control the horizontal stabilizer.

3. The horizontal stabilizer balancing control method as described in claim 1, characterized in that, When one of the channel computers in the first channel of the first trim channel and the second channel computer in the second trim channel fails, the horizontal stabilizer trim control method further includes: Control commands for the horizontal stabilizer are received from the flight control computer by the first channel computer in the first trim channel and another non-failed channel computer in the second trim channel; The control commands are transmitted from the other non-failure channel computer to the corresponding balance electronic controller; and The corresponding balancing electronic controller outputs the control command to the actuator to control the horizontal stabilizer.

4. The horizontal stabilizer balancing control method as described in claim 1, characterized in that, When both the first channel computer in the first trim channel and the second channel computer in the second trim channel fail, the horizontal stabilizer trim control method further includes: In response to receiving a manual trim signal from the manual trim switch, the first trim electronic controller in the first trim channel and the second trim electronic controller in the second trim channel output a main control command to the actuator to control the horizontal stabilizer.

5. The horizontal stabilizer balancing control method as described in claim 4, characterized in that, The horizontal stabilizer trim control method further includes: a backup trim electronic controller, predetermined from the first trim electronic controller and the second trim electronic controller, outputting a backup control command to the actuator, wherein the backup control command includes releasing the corresponding brake.

6. The horizontal stabilizer balancing control method as described in claim 4, characterized in that, The first and second trim electronic controllers interact via a third bus to prevent simultaneous trimming of both channels.

7. A horizontal stabilizer trim control system for performing the method as described in any one of claims 1-6, comprising: Flight control computer; A first trim channel and a second trim channel are coupled to the flight control computer. The first trim channel includes a first channel computer, a first trim electronic controller, and a first control module, while the second trim channel includes a second channel computer, a second trim electronic controller, and a second control module. The flight control computer is configured to master the first trim channel and the second trim channel. as well as An actuator coupled to the horizontal stabilizer, wherein the first control module and the second control module are coupled to the actuator and control the actuator to control the balancing of the horizontal stabilizer.

8. The horizontal stabilizer balancing control system as described in claim 7, characterized in that, Further includes: A manual trim switch coupled between the first trim channel and the second trim channel.

9. The horizontal stabilizer balancing control system as described in claim 7, characterized in that, Either the first trim electronic controller or the second trim electronic controller includes: a bus signal processing module, a discrete signal processing module, a rate calculation module, a primary / backup determination module, a motor control module, and a brake control module.

10. The horizontal stabilizer balancing control system as described in claim 7, characterized in that: Both the first channel computer in the first trim channel and the second channel computer in the second trim channel are coupled to the flight control computer via a first bus; The first channel computer is coupled to the first trim electronic controller via a second bus, and the second channel computer is coupled to the second trim electronic controller via a second bus; and The first trim electronic controller is coupled to the second trim electronic controller via a third bus.

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