A method and apparatus for indicating the trim state of a horizontal stabilizer

Abstract

Disclosed are a method and device for prompting a horizontal stabilizer trim state, which add a corresponding trim display when a "horizontal stabilizer failure" and "current trim position inconsistent with optimal trim position" alarm is triggered, so as to better meet the requirements of aviation safety regulations for alarms.

Description

Technical Field

[0001] This invention relates to the field of fly-by-wire flight control technology, and more particularly to a method and apparatus for indicating the trim status of a horizontal stabilizer. Background Technology

[0002] During flight, the optimal trim position is crucial for aircraft fuel consumption and performance. If the trim deviates from the center-based optimal trim position, aerodynamic efficiency may decrease or even affect flight control stability. For some advanced mainstream aircraft models, before takeoff, in addition to manual trim by the pilot, the flight control computer can automatically trim the horizontal stabilizer to the optimal position under the current weight and center of gravity by having the pilot manually input information such as the takeoff center of gravity from the manifest. For horizontal stabilizer failure, relevant aircraft models currently operating in the civil aviation market typically have corresponding alarms (usually CAUTION level alarms). With the addition of the automatic horizontal stabilizer trim function while the aircraft is on the ground, a matching "Trim position does not match optimal position" CAUTION level alarm has been added. If the difference between the trimmed position and the optimal position calculated by the fuel system is significant, a "Trim position does not match optimal position" CAUTION level alarm will be triggered.

[0003] For the trim indication of the horizontal stabilizer, any of the following methods are typically used to maintain consistency between the trim indication color and the warning color, thereby meeting airworthiness requirements:

[0004] a) The trim indication method is EI constant display, which is displayed as a yellow cross when the horizontal stabilizer fails or displays the corresponding position when the horizontal stabilizer fails.

[0005] b) Configure the automatic jump logic of the simplified diagram page. When the horizontal stabilizer fails, the simplified diagram page will automatically jump to the flight control page, and the horizontal stabilizer will be displayed in yellow.

[0006] The alarm levels for "Horizontal stabilizer control failure" and "Trim position mismatch with optimal position" are the same. To avoid confusion for the crew, if two different horizontal stabilizer status display mechanisms are used, the display logic will be complex, there will be some design redundancy, and the flight load of the crew will also increase.

[0007] Therefore, there is a need in the art for improved display methods and apparatus for indicating the balancing status of horizontal stabilizers. Summary of the Invention

[0008] This proposal discloses a method and apparatus for indicating the trim status of the horizontal stabilizer. It adds trim display corresponding to the triggering of alarms such as "horizontal stabilizer failure" and "current trim position is inconsistent with the optimal trim position" for the horizontal stabilizer trim indication on the aircraft cockpit display, which better meets the alarm requirements in aviation safety regulations.

[0009] In one embodiment of the present invention, an apparatus for indicating the trim status of a horizontal stabilizer is provided, comprising: a trim calculation module for determining a trim indication scheme for the horizontal stabilizer, the trim indication scheme including a permissible trim range for normal takeoff and an optimal trim range; a constant display module for displaying the name and scale of the constant display module on a display component; an optimal trim status display module for indicating the optimal trim range for normal takeoff on the scale according to the trim indication scheme; and a pointer display module for indicating the current trim position of the horizontal stabilizer determined according to a trim position signal on the scale via a pointer, wherein when the aircraft is in the ground phase and water... When the horizontal stabilizer is working normally: if the current balancing position of the horizontal stabilizer is within the optimal balancing range, the optimal balancing status display module indicates the optimal balancing range with a first color, and the pointer display module indicates the current balancing position of the horizontal stabilizer with a pointer of a second color. If the current balancing position of the horizontal stabilizer is not within the optimal balancing range, the optimal balancing status display module indicates the optimal balancing range with a third color, and the pointer display module indicates the current balancing position of the horizontal stabilizer with a pointer of the third color. The third color is different from the first color and the second color.

[0010] In one aspect, the device for indicating the trim status of the horizontal stabilizer further includes: a permissible trim range display module, wherein when the aircraft is on the ground, if the set trim position is within the permissible trim range, the permissible trim range display module indicates the permissible trim range on the scale, and when the aircraft is in the air, the permissible trim range display module does not display the permissible trim range.

[0011] In one aspect, the allowable balancing range display module indicates the allowable balancing range with the second color.

[0012] On one hand, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer is working normally, the constant display module displays the name of the constant display module and the scale in the fourth color; when the horizontal stabilizer fails, the constant display module displays the name of the constant display module in the third color.

[0013] On one hand, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer fails but the trim position signal is valid, the constant display module displays the name of the constant display module in the third color, and the pointer display module indicates the current trim position of the horizontal stabilizer or the last valid current trim position reading with a pointer in the third color.

[0014] On one hand, for the aircraft during the ground phase or the air phase: when the trim position signal is lost, the pointer display module replaces the pointer with a cross of the third color.

[0015] On one hand, the pointer display module displays a value representing the current balancing position of the horizontal stabilizer in the same color as the pointer.

[0016] In one embodiment of the present invention, a method for indicating the trim status of a horizontal stabilizer is provided, comprising: determining a trim indication scheme for the horizontal stabilizer, the trim indication scheme including a permissible trim range for normal takeoff and an optimal trim range; displaying a name and a scale for the trim status of the horizontal stabilizer on a display component; indicating the optimal trim range for normal takeoff on the scale according to the trim indication scheme; and indicating the current trim position of the horizontal stabilizer determined according to a trim position signal on the scale by a pointer, wherein when the aircraft is in the ground phase and the horizontal stabilizer is operating normally: if the current trim position of the horizontal stabilizer is within the optimal trim range, the optimal trim range is indicated with a first color, and the current trim position of the horizontal stabilizer is indicated with a pointer of a second color; if the current trim position of the horizontal stabilizer is not within the optimal trim range, the optimal trim range is indicated with a third color, and the current trim position of the horizontal stabilizer is indicated with a pointer of the third color, the third color being different from the first color and the second color.

[0017] In one aspect, the method for indicating the trim status of the horizontal stabilizer further includes: when the aircraft is on the ground, indicating the allowable trim range on the scale if the set trim position is within the allowable trim range, and not displaying the allowable trim range when the aircraft is in the air.

[0018] On one hand, the second color indicates the permissible balancing range.

[0019] On one hand, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer is functioning normally, the name and the scale are displayed in the fourth color; when the horizontal stabilizer malfunctions, the name is displayed in the third color.

[0020] On one hand, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer fails but the trim position signal is valid, the name is displayed in the third color, and the current trim position of the horizontal stabilizer or the last valid current trim position reading is indicated by a pointer in the third color.

[0021] On the one hand, for aircraft in the ground phase or in the air phase: when the trim position signal is lost, the pointer is replaced with a cross of the third color.

[0022] On the one hand, a value representing the current balancing position of the horizontal stabilizer is displayed in the same color as the pointer.

[0023] On the one hand, the first color, the second color, the third color, and the fourth color can be different.

[0024] This proposal offers the following advantages: Based on existing aircraft trim indications, it incorporates a constant display and adds trim displays corresponding to alarms such as "Horizontal stabilizer failure" and / or "Current trim position inconsistent with optimal trim position," providing a more intelligent and intuitive indication of the crew's horizontal stabilizer trim status and enabling error correction. Furthermore, this scheme uses a single trim indication to differentiate between two alarms of the same level and color, better complying with aviation safety regulations, increasing the integration of cockpit displays, and establishing a potentially feasible solution for future wide-body aircraft development. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the structure of a device for indicating the balancing status of a horizontal stabilizer according to an embodiment of the present invention.

[0026] Figure 2 This is a schematic diagram of the display of a constant display module according to an embodiment of the present invention.

[0027] Figure 3 This is a schematic diagram of a pointer display module according to an embodiment of the present invention.

[0028] Figure 4 This is a schematic diagram of the display of the allowable balancing range display module according to an embodiment of the present invention.

[0029] Figure 5 This is a schematic diagram of the optimal balance state display module according to an embodiment of the present invention.

[0030] Figure 6 This is a schematic diagram of a fault display module according to an embodiment of the present invention.

[0031] Figure 7 This is a schematic diagram showing the loss of the balancing position signal according to an embodiment of the present invention.

[0032] Figure 8 This is a schematic diagram showing the balancing status when the current balancing position is within the optimal balancing range, according to an embodiment of the present invention.

[0033] Figure 9 This is a schematic diagram showing that the current balancing position is not within the optimal balancing range according to an embodiment of the present invention.

[0034] Figure 10 This is a schematic diagram showing the current balancing position within the optimal balancing range but the horizontal stabilizer has failed, according to an embodiment of the present invention.

[0035] Figure 11 This is a schematic diagram illustrating the failure of an aerial horizontal stabilizer according to an embodiment of the present invention.

[0036] Figure 12 This is a schematic diagram showing the loss of the balancing position signal according to an embodiment of the present invention.

[0037] Figure 13 This is a schematic diagram showing a horizontal stabilizer failure and loss of the trim position signal according to an embodiment of the present invention.

[0038] Figure 14 This is a flowchart of a method for indicating the balancing status of a horizontal stabilizer according to an embodiment of the present invention. Detailed Implementation

[0039] The present invention will be further described below with reference to specific embodiments and accompanying drawings, but this should not be construed as limiting the scope of protection of the present invention.

[0040] Figure 1 This is a schematic diagram of an apparatus for indicating the trim status of a horizontal stabilizer according to an embodiment of the present invention. The apparatus can be implemented by a flight control system. The apparatus may include a trim status identification module 110, a flight phase identification module 120, a trim calculation module 130, a display control component 150, a trim fault alarm component 140, a display 160, etc. The display control component 150 may be a separate display control device from the display 160, or it may be part of the display 160. Display 1 and Display 2 may be separate displays, or they may be different display areas of the same display.

[0041] For the horizontal stabilizer, pilots can manually trim it using trim switches, or the flight control computer can automatically trim the horizontal stabilizer via control laws. Pilots send manual pitch trim control inputs via pitch trim switches and / or the aircraft control laws calculate automatic control inputs based on aircraft attitude, configuration, and speed signals. The trim control signals provided by the pilot or flight control computer are transmitted to the horizontal stabilizer control unit to trim the horizontal stabilizer to the optimal position under the current weight and center of gravity. In the air, horizontal stabilizer control enables elevator unloading; on the ground and during leveling, it enables manual pitch trim.

[0042] The horizontal stabilizer control device monitors the state of the horizontal stabilizer. The device can detect the state of the horizontal stabilizer through a sensor network (e.g., position sensors, speed sensors, load sensors, temperature sensors, etc.) and monitoring logic. By way of example and not limitation, a position sensor mounted on the trim actuator or horizontal stabilizer drive mechanism detects the actual position of the horizontal stabilizer and generates a horizontal stabilizer trim position signal to indicate the current angular position of the horizontal stabilizer. The horizontal stabilizer control device can receive the horizontal stabilizer trim position signal generated by the position sensor and transmit it to the trim calculation module 130. The horizontal stabilizer control device can also generate horizontal stabilizer operating signals (e.g., indicating the horizontal stabilizer operating state, such as position, speed, load, temperature, etc.) based on various parameters of the detected horizontal stabilizer.

[0043] The horizontal stabilizer control device can send the horizontal stabilizer operating signal and the horizontal stabilizer balancing position signal to the balancing status identification module 110. The balancing status identification module 110 is configured to monitor the horizontal stabilizer based on the horizontal stabilizer operating signal and the horizontal stabilizer balancing position signal, integrate and compare data from multiple sensors in the horizontal stabilizer control device, and determine whether the horizontal stabilizer has actually failed, such as whether a "horizontal stabilizer control failure" fault has occurred.

[0044] For example, the balancing status identification module 110 determines whether the horizontal stabilizer working signal and the horizontal stabilizer balancing position signal are valid. If both signals are valid, but the horizontal stabilizer working signal indicates that the current horizontal stabilizer is in a fault state, then the fault condition is fed back to the balancing calculation module 130.

[0045] The flight phase identification module 120 can identify the current flight phase of the aircraft based on parameters such as wheel-mounted signals. Flight phases may include ground phases and air phases. The flight phase identification module 120 can send the flight phase identification results to the flight control computer and display control component 150. The flight phase identification results will serve as an important reference for the trim calculation module 130 in displaying the trim status.

[0046] The trim calculation module 130 can determine the relationship between the actual position of the horizontal stabilizer, the permissible trim range value on the ground (e.g., often referred to as the green belt), and the optimal trim range value, and send the aforementioned trim display information to the display control component 150. In one embodiment, the trim calculation module 130 can perform calculations based on a preset algorithm and model, taking into account important flight parameters such as flight phase, flight conditions, aircraft load, center of gravity, and atmospheric data, according to the input from the trim state identification module 110, and transmit the calculation results (i.e., the trim indication scheme) to the display control component 150. The trim indication scheme includes the permissible trim range and the optimal trim range. In one embodiment, the trim indication scheme includes the trim position (e.g., the desired trim position).

[0047] In one embodiment, if the trim status identification module 110 identifies that the horizontal stabilizer control function is normal (normal operation), the trim calculation module 130 calculates whether the "actual position" (based on the horizontal stabilizer trim position signal transmitted from the horizontal stabilizer control device) and the "expected position" (the trim position calculated by the trim calculation module) are consistent.

[0048] In one embodiment, the balancing calculation module 130 compares the actual position with the optimal balancing range value based on the balancing calculation result. If the actual position is not within the optimal balancing range, it determines that an alarm "the current balancing position is inconsistent with the optimal balancing position" should be triggered.

[0049] When the trim calculation module 130 determines that a trim fault has occurred, such as "horizontal stabilizer failure" or "current trim position is inconsistent with the optimal trim position," the trim fault alarm component 140 provides corresponding alarm information to remind the pilot to make timely adjustments. The alarm information can be displayed on the display 2 (normal display), including "horizontal stabilizer failure" and "current trim position is inconsistent with the optimal trim position."

[0050] The display control component 150 receives the trim calculation results from the trim calculation module 130 and displays the trim status information of the horizontal stabilizer on the display 1 (normal display) to intuitively show the current trim status and ideal trim status of the horizontal stabilizer. It can use various methods such as digital display and graphical display to present the trim status information to the pilot in an easy-to-understand format. The display control component 150 can use different modes to display the trim status information of the horizontal stabilizer at different flight phases (e.g., based on the flight phase identification module 120).

[0051] The display control component 150 may include, but is not limited to, a constant display module, a permissible balancing range display module, an optimal balancing display module, a pointer display module, and a fault display module.

[0052] The constant display module is configured to continuously display trim (TRIM) status information on the display, including the name of the constant display module and its scale. Except in the event of a TRIM failure, the trim status information is continuously displayed on the display so that the pilot can constantly monitor the trim status to ensure flight safety. (Reference) Figure 2 The content displayed by the constant display module may include the name (e.g., STAB, indicating the horizontal stabilizer); a scale; a direction indicator (NU indicates nose up, ND indicates nose down); and a trim indication range of -XX° (NU) to +YY° (ND). When the horizontal stabilizer is working normally, the constant display module can specify a color (e.g., white) to display the name and scale of the constant display module.

[0053] The pointer display module indicates the current balancing position of the horizontal stabilizer on the scale of the constant display module via a pointer. The horizontal stabilizer balancing position signal generated by the position sensor can be transmitted from the horizontal stabilizer control device to the balancing calculation module 130, and then to the pointer display module, thus indicating the current balancing position of the horizontal stabilizer on the scale. The pointer display module can also display a numerical value representing the current balancing position in association with the pointer. The pointer display module can display the numerical value representing the current balancing position of the horizontal stabilizer in the same color as the pointer. Figure 3 This is a schematic diagram of a pointer display module according to an embodiment of the present invention.

[0054] The permissible trim range display module indicates the permissible trim range for normal takeoff on the scale of the constant display module based on the results of the trim calculation module 130. Figure 4 This is a schematic diagram of the permissible trim range display module according to an embodiment of the present invention. In some embodiments, a green display, referred to as a green band, may be used in accordance with relevant airworthiness regulations; the range is -AA° (NU) to +BB° (ND). The permissible trim range display module is displayed only during the ground phase and not during the air phase.

[0055] The optimal trim status display module indicates the optimal trim range for normal takeoff on the scale of the constant display module based on the results of the trim calculation module 130. Figure 5 This is a schematic diagram of an optimal trim state display module according to an embodiment of the present invention. In one embodiment, the range scale may be displayed in magenta or according to the aircraft's color scheme. The optimal trim range is displayed only during the ground phase and not during the air phase.

[0056] The fault display module can receive feedback information related to the fault of the horizontal stabilizer control device from the balancing calculation module 130, and display the fault information interface on the information displayed in the constant display module.

[0057] Figure 6This is a schematic diagram of a fault display module according to an embodiment of the present invention. For example, when the aircraft is in the air and the horizontal stabilizer fails but the trim position signal is valid, the reading remains at the last valid reading, and the name, pointer, and reading of the constantly displayed module are all in an alarm color (e.g., amber).

[0058] Figure 7 This is a schematic diagram illustrating the display of a lost trim position signal according to an embodiment of the present invention. Whether on the ground or in the air, when the horizontal stabilizer trim position signal is lost, the fault display module replaces the pointer and value of the pointer module with an "X" (e.g., an amber "X").

[0059] According to one embodiment, when the aircraft is in the ground phase and the horizontal stabilizer is operating normally, if the current trim position of the horizontal stabilizer is within the optimal trim range, the optimal trim status display module indicates the optimal trim range in a first color (e.g., magenta), and the pointer display module indicates the current trim position of the horizontal stabilizer with a pointer in a second color (e.g., green). When the aircraft is in the ground phase, the permissible trim range display module indicates the permissible trim range on a scale, for example, by using the second color (e.g., green).

[0060] Figure 8 This is a schematic diagram showing the trim status when the current trim position is within the optimal trim range, according to an embodiment of the present invention. The aircraft is in the ground phase, the trim position is within the green zone and the current trim position is within the optimal trim range, and the horizontal stabilizer is functioning normally: the name of the constant display module is white, and the numerical value and pointer are green; the pointer overlaps with the magenta optimal trim display module.

[0061] If the current balancing position of the horizontal stabilizer is not within the optimal balancing range, the optimal balancing state display module indicates the optimal balancing range with a third color (e.g., amber), and the pointer display module indicates the current balancing position of the horizontal stabilizer with a pointer of a third color (e.g., amber), which is different from the first color (e.g., magenta) and the second color (e.g., green).

[0062] Figure 9 This is a schematic diagram showing the trim status when the current trim position is not within the optimal trim range according to an embodiment of the present invention. When the aircraft is on the ground, the trim position is within the green zone, the current trim position is not within the optimal trim range, and the horizontal stabilizer is operating normally: the name of the constant display module is white, the pointer and value of the optimal trim range display module and the pointer display module are amber, and the pointer is not within the magenta optimal trim range.

[0063] refer to Figure 3During the ground or air phases of the aircraft, when the horizontal stabilizer is functioning normally, the constant display module displays its name and scale in the fourth color (white), and the pointer display module displays the pointer and reading in the fourth color (white). When the horizontal stabilizer malfunctions, the constant display module displays its name in the third color (amber). During the ground or air phases of the aircraft, when the horizontal stabilizer malfunctions but the trim position signal is valid, the constant display module displays its name in the third color (amber), and the pointer display module indicates the current trim position or the last valid current trim position reading of the horizontal stabilizer using a pointer in the third color (amber).

[0064] Figure 10 This is a schematic diagram illustrating the trim status display when the current trim position is within the optimal trim range but the horizontal stabilizer is in failure, according to an embodiment of the present invention. When the aircraft is in the ground phase, the trim position is within the green zone, the current trim position is within the optimal trim range, and the horizontal stabilizer is in failure: the name of the constant display module is amber, the pointer and value of the pointer display module are amber, and the pointer overlaps with the magenta optimal trim range.

[0065] Figure 11 This is a schematic diagram illustrating the trim status display during an in-flight horizontal stabilizer failure, according to an embodiment of the present invention. When the aircraft is in the air and the horizontal stabilizer fails but the trim position signal is valid, the reading remains at the last valid reading, and the name, pointer, and reading of the constantly displayed module are all amber. Furthermore, during the in-flight phase, the permissible trim range and optimal trim range are not displayed.

[0066] When the trim position signal is lost during the ground or air phase of the aircraft, the pointer display module replaces the pointer with a cross of the third color (amber). Figure 12 This is a schematic diagram illustrating an invalid horizontal stabilizer trim value display according to an embodiment of the present invention. The horizontal stabilizer functions normally, whether on the ground or in the air, but the trim position signal is lost: the name of the normally displayed module is white, but the pointer and numerical value are replaced by an amber "X".

[0067] Figure 13 This is a schematic diagram of a display indicating a horizontal stabilizer failure and loss of trim position signal according to an embodiment of the present invention. Whether on the ground or in the air, in the event of a horizontal stabilizer failure and loss of trim position signal: the name of the constant display module is amber, and the pointer and numerical value are replaced by an amber "X".

[0068] Figure 14 This is a flowchart of a method 1400 for indicating the trim status of a horizontal stabilizer according to an embodiment of the present invention. This method can be implemented by a flight control system.

[0069] In step 1402, a trim indication scheme for the horizontal stabilizer can be determined, which includes the permissible trim range for normal takeoff and the optimal trim range.

[0070] In step 1404, the name and scale for the horizontal stabilizer balance state are displayed on the display component.

[0071] In step 1406, the optimal trim range for normal takeoff is indicated on the scale according to the trim instruction scheme.

[0072] In step 1408, the pointer indicates the current balancing position of the horizontal stabilizer determined according to the balancing position signal on the scale.

[0073] In one embodiment, when the aircraft is in the ground phase and the horizontal stabilizer is functioning normally: if the current trim position is within the optimal trim range, the optimal trim range is indicated by a first color, and the current trim position of the horizontal stabilizer is indicated by a pointer of a second color. If the current trim position of the horizontal stabilizer is not within the optimal trim range, the optimal trim range is indicated by a third color, and the current trim position of the horizontal stabilizer is indicated by a pointer of a third color, which differs from the first and second colors.

[0074] In one embodiment, the numerical value representing the current balancing position of the horizontal stabilizer is displayed in the same color as the pointer.

[0075] In one embodiment, the permissible trim range is indicated on a scale when the aircraft is in the ground phase, and is not displayed when the aircraft is in the air phase.

[0076] In one embodiment, a second color indicates the permissible balancing range.

[0077] In one embodiment, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer is functioning normally, the name and scale are displayed in a fourth color; when the horizontal stabilizer malfunctions, the name is displayed in a third color.

[0078] In one embodiment, for the aircraft during the ground phase or the air phase: when the horizontal stabilizer fails but the trim position signal is valid, the name is displayed in a third color, and the current trim position of the horizontal stabilizer or the last valid current trim position reading is indicated by a pointer in a third color.

[0079] In one embodiment, for the aircraft during the ground phase or the air phase: when the trim position signal is lost, a cross of the third color is used instead of the pointer.

[0080] The above examples are merely preferred embodiments of the horizontal stabilizer balancing state display logic proposed in this aspect, but the scope of protection of this invention is not limited thereto. The various specific display colors given herein are merely examples and do not limit the scope of protection of this invention. Those skilled in the art can make various modifications as needed, and these modifications fall within the scope of this invention.

[0081] This proposal discloses a display component and device for indicating the trim status of the horizontal stabilizer. Based on existing trim displays for mainstream aircraft models, it features a constant display and innovatively adds trim displays corresponding to the triggering of "horizontal stabilizer failure" and "current trim position inconsistent with optimal trim position" alarms. Furthermore, using different visual elements for trim indication allows for differentiation between these two alarms of the same level and the same warning color, better complying with the airworthiness requirements for color consistency between alarms and displays, and increasing the integration of cockpit displays.

[0082] The present invention provides a horizontal stabilizer balancing status display logic, which can be expressed in various forms including but not limited to digital display, analog pointer display and graphic display. It allows for a variety of alternative designs, such as single color, multi-color or flashing colors to enhance the visual effect, and shapes such as circles, rectangles or irregular shapes.

[0083] This device is innovative in both visual cues and indication of compliance with terms, as detailed below:

[0084] Innovation Point 1: This device displays the horizontal stabilizer trim status of the aircraft under various conditions on the ground and in the air through a constant-display horizontal stabilizer trim indicator, helping the crew to quickly identify and understand the current horizontal stabilizer status. In particular, this device can hierarchically process two alarms of the same level and with the same indicator color: when "Horizontal Stabilizer Failure" is triggered, an amber label, along with an amber reading and reading box, is displayed; when "Current Trim Position Does Not Match Optimal Trim Position" is triggered, an amber optimal trim range, along with an amber reading and reading box, is displayed. In the visual channel, color is the most intuitive information; this device helps the crew quickly identify horizontal stabilizer-related alarms, further improving the identifiability and urgency differentiation of alarms.

[0085] Innovation Point 2: This device optimizes the horizontal stabilizer trim display in the constant display area. When "Horizontal stabilizer failure" is triggered, it displays an amber "STAB" message, along with an amber reading and reading box. At this time, the CAS alarm for "Horizontal stabilizer failure" is also amber. When "Current trim position is inconsistent with optimal trim position" is triggered, it displays the optimal trim range, along with an amber reading and reading box. At this time, the CAS alarm for "Current trim position is inconsistent with optimal trim position" is also amber. This facilitates rapid alarm identification by the flight crew, improves the consistency of alarm display, and enables the flight crew to detect changes in the trim system status more promptly and accurately, and even correct errors, thereby enhancing the crew's situational awareness.

[0086] Innovation Point 3: This device optimizes the horizontal stabilizer trim display in the constant display area, effectively integrating two alarm messages into the trim display area, which increases the integration of the cockpit display. The benefit is that the crew no longer needs to switch between multiple information sources, reducing the crew's reaction time and improving decision-making efficiency.

[0087] This invention aims to construct a fundamental display logic framework, facilitating diverse display design and innovation based on specific needs. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this invention should be included within the protection scope of this invention. Therefore, the protection scope of this invention should be determined by the scope of the claims.

[0088] The various steps and modules of the methods and apparatus described above can be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in connection with this disclosure can be implemented or executed using a general-purpose processor, digital signal processor (DSP), application-specific integrated circuit (ASIC), field-programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. A general-purpose processor can be a processor, microprocessor, controller, microcontroller, or state machine, etc. If implemented in software, the various illustrative steps and modules described in connection with this disclosure can be stored as one or more instructions or codes on a computer-readable medium or transmitted. Software modules implementing the various operations of this disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, removable disk, CD-ROM, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium and execute the corresponding program modules to implement the various steps of this disclosure.

[0089] The numerical values ​​given in the various embodiments are merely examples and are not intended to limit the scope of the invention. In practice, the specific parameters of each component and various thresholds can be appropriately set as needed, and are not limited to the specific values ​​given as examples herein. Furthermore, as a whole technical solution, there are other components or steps not listed in the claims or specification of this invention. Moreover, a single name for a component does not preclude other names for that component.

[0090] It should also be noted that these embodiments may be described as processes depicted as flowcharts, flow diagrams, structure diagrams, or block diagrams. Although a flowchart may describe the operations as a sequential process, many of these operations can be executed in parallel or concurrently. Furthermore, the order of these operations can be rearranged.

[0091] The directional terms used in the description of this application, such as "front, back, up, down, left, right", "horizontal, vertical, horizontal", "top, bottom", "inner, outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of this application.

[0092] Furthermore, it should be noted that the use of sequential terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this application.

[0093] The disclosed methods, apparatuses, and systems should not be limited in any way. Rather, this disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (individually and in various combinations and sub-combinations of each other). The disclosed methods, apparatuses, and systems are not limited to any particular aspect or feature or combination thereof, and no disclosed embodiment is required to have any one or more specific advantages or to solve any particular or all technical problems.

[0094] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the scope of protection of the present invention.

Claims

1. A device for indicating the balancing status of a horizontal stabilizer, characterized in that, include: The trim calculation module is used to determine the trim indication scheme for the horizontal stabilizer, which includes the allowable trim range for normal takeoff and the optimal trim range. A constant display module is used to display the name and scale of the constant display module on the display component; The optimal trim status display module indicates the optimal trim range for normal takeoff on the scale according to the trim indication scheme. The pointer display module indicates the current balancing position of the horizontal stabilizer, determined based on the balancing position signal, on the scale via a pointer. When the aircraft is in the ground phase and the horizontal stabilizer is functioning normally: If the current balancing position of the horizontal stabilizer is within the optimal balancing range, the optimal balancing status display module indicates the optimal balancing range with a first color, and the pointer display module indicates the current balancing position of the horizontal stabilizer with a pointer of a second color. If the current balancing position of the horizontal stabilizer is not within the optimal balancing range, the optimal balancing status display module indicates the optimal balancing range with a third color, and the pointer display module indicates the current balancing position of the horizontal stabilizer with a pointer of the third color, wherein the third color is different from the first color and the second color. Specifically, this applies to the aircraft's operation during the ground phase or the air phase: When the horizontal stabilizer is working normally, the constant display module displays the name of the constant display module and the scale in the fourth color; When the horizontal stabilizer fails, the constant display module displays its name in the third color; When the horizontal stabilizer fails but the balancing position signal is valid, the constant display module displays the name of the constant display module in the third color, and the pointer display module indicates the current balancing position of the horizontal stabilizer or the last valid current balancing position reading with a pointer of the third color.

2. The device for indicating the balancing status of a horizontal stabilized surface as described in claim 1, characterized in that, Also includes: A permissible trim range display module, wherein when the aircraft is on the ground, the permissible trim range display module indicates the permissible trim range on the scale, and when the aircraft is in the air, the permissible trim range display module does not display the permissible trim range.

3. The device for indicating the balancing status of a horizontal stabilizer as described in claim 2, characterized in that: The allowable balancing range display module indicates the allowable balancing range with the second color.

4. The device for indicating the balancing status of a horizontal stabilized surface as described in claim 1, characterized in that, For aircraft during the ground phase or the air phase: When the balancing position signal is lost, the pointer display module replaces the pointer with a cross of the third color.

5. The device for indicating the balancing status of a horizontal stabilizer as described in any one of claims 1 to 4, characterized in that: The pointer display module displays a value representing the current balancing position of the horizontal stabilizer in the same color as the pointer.

6. A method for indicating the balancing status of a horizontal stabilized surface, characterized in that, include: Determine the trim indication scheme for the horizontal stabilizer, the trim indication scheme including the allowable trim range and the optimal trim range for normal takeoff; The display component shows the name and scale used for the leveling state of the horizontal stabilizer; The optimal trim range for normal takeoff is indicated on the scale according to the trim indication scheme. The pointer on the scale indicates the current balancing position of the horizontal stabilizer, determined based on the balancing position signal. When the aircraft is in the ground phase and the horizontal stabilizer is functioning normally: If the current balancing position of the horizontal stabilizer is within the optimal balancing range, then the optimal balancing range is indicated by a first color, and the current balancing position of the horizontal stabilizer is indicated by a pointer of a second color. If the current balancing position of the horizontal stabilizer is not within the optimal balancing range, then the optimal balancing range is indicated by a third color, and the current balancing position of the horizontal stabilizer is indicated by a pointer of the third color, which is different from the first and second colors. Specifically, this applies to the aircraft's operation during the ground phase or the air phase: When the horizontal stabilizer is working normally, the name and the scale are displayed in the fourth color; When the horizontal stabilizer fails, the name is displayed in the third color; When the horizontal stabilizer fails but the trim position signal is valid, the name is displayed in the third color, and the pointer in the third color indicates the current trim position of the horizontal stabilizer or the last valid current trim position reading.

7. The method for indicating the balancing status of a horizontal stabilized surface as described in claim 6, characterized in that, Also includes: When the aircraft is on the ground, the permissible trim range is indicated on the scale, and when the aircraft is in the air, the permissible trim range is not displayed.

8. The method for indicating the balancing status of a horizontal stabilizer as described in claim 7, characterized in that: The second color indicates the permissible balancing range.

9. The method for indicating the balancing status of a horizontal stabilizer as described in claim 6, characterized in that, For aircraft during the ground phase or the air phase: When the balancing position signal is lost, the pointer is replaced by a cross of the third color.

10. The method for indicating the balancing status of a horizontal stabilizer as described in any one of claims 6 to 9, characterized in that: The numerical value representing the current balancing position of the horizontal stabilizer is displayed in the same color as the pointer.

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