lock the bank angle parameter and the ground speed parameter

Abstract

This application relates to locking a bank angle parameter and a ground speed parameter. A flight management system (FMS) of an aircraft can determine that a leg of a lateral trajectory profile of a flight plan of the aircraft is active. The FMS can determine, based on determining that the leg of the lateral trajectory profile is active, that a lateral distance between the aircraft and an end waypoint associated with the leg satisfies a lateral distance threshold, and therefore can perform an update to the lateral trajectory profile to lock a bank angle parameter to a particular bank angle value. The FMS can determine that a transition associated with the end waypoint and another leg of the lateral trajectory profile is active, and therefore can perform an update to the lateral trajectory profile to lock a ground speed parameter to a particular ground speed value.

Description

Technical Field

[0001] This disclosure generally relates to the flight management system (FMS) of an aircraft and the FMS that locks tilt angle parameters and ground speed parameters. Background Technology

[0002] The lateral trajectory profile of a flight plan provides information about lateral turns and transition areas between waypoints and other navigation points identified in the flight plan. The aircraft's FMS determines the turning radius of the transition area based on the aircraft's ground speed and its bank angle. Summary of the Invention

[0003] In some implementations, the aircraft's FMS includes one or more memories; and one or more processors communicatively coupled to the one or more memories, configured to: determine that a leg of the lateral trajectory profile associated with the aircraft's flight plan is active; based on the determination that the leg of the lateral trajectory profile is active, determine that the lateral distance between the aircraft and the end waypoint associated with the leg meets a lateral distance threshold; based on the determination that the lateral distance meets the lateral distance threshold, perform an update on the lateral trajectory profile to lock the bank angle parameter to a specific bank angle value; determine that a transition associated with the end waypoint and another leg of the lateral trajectory profile is active, and that the leg is active; and based on the determination that the transition is active and that the leg is active, perform an update on the lateral trajectory profile to lock the ground speed parameter to a specific ground speed value.

[0004] In some embodiments, a non-transitory computer-readable medium storing a set of instructions, including one or more instructions that, when executed by one or more processors of the aircraft's FMS, cause the FMS to: determine that a segment of a lateral trajectory profile associated with the aircraft's flight plan is active; based on the determination that the segment of the lateral trajectory profile is active, determine a lateral distance threshold associated with the end waypoint of the segment; determine whether the lateral distance between the aircraft and the end waypoint satisfies the lateral distance threshold; and selectively perform one of the following operations: based on the determination that the lateral distance satisfies the lateral distance threshold, perform a first update to the lateral trajectory profile to lock the tilt angle parameter to a specific tilt angle value to which the aircraft's tilt angle has been set, or based on the determination that the lateral distance does not satisfy the lateral distance threshold, perform a second update to the lateral trajectory profile to set the tilt angle parameter to another tilt angle value.

[0005] In some implementations, a method includes determining, by the aircraft's FMS, whether the lateral distance between the aircraft and the end waypoint of the segment is active based on whether the segment of the lateral trajectory profile is active; and selectively performing one of the following operations: first updating the lateral trajectory profile based on the determination that the lateral distance meets the lateral distance threshold to lock the tilt angle parameter to a specific tilt angle value, or second updating the lateral trajectory profile based on the determination that the lateral distance does not meet the lateral distance threshold to set the tilt angle parameter to another tilt angle value.

[0006] The following provides an overview of some aspects of this disclosure: In one aspect, the FMS of an aircraft includes: one or more memories; and one or more processors communicatively coupled to the one or more memories, configured to: determine that a segment of the lateral trajectory profile associated with the aircraft's flight plan is active; based on the determination that the segment of the lateral trajectory profile is active, determine that the lateral distance between the aircraft and the endpoint waypoint associated with the segment satisfies a lateral distance threshold; based on the determination that the lateral distance satisfies the lateral distance threshold, perform an update on the lateral trajectory profile to lock the bank angle parameter to a specific bank angle value; determine that a transition associated with the endpoint waypoint and another segment of the lateral trajectory profile is active, and that the segment is active; and based on the determination that the transition is active and that the segment is active, perform an update on the lateral trajectory profile to lock the ground speed parameter to a specific ground speed value.

[0007] In another aspect, one or more processors are also configured to determine the transition turning radius based on the tilt angle parameter and the ground speed parameter, which will be fixed until the flight segment is no longer active.

[0008] In another aspect, one or more processors are also configured to: determine that the segment of the lateral trajectory profile is no longer active; and based on the fact that the segment of the lateral trajectory profile is no longer active, perform an update on the lateral trajectory profile to unlock the tilt angle parameter and unlock the ground speed parameter.

[0009] In another aspect, one or more processors are also configured to: after updating the lateral trajectory profile to unlock the bank angle parameter and the ground speed parameter, and based on the roll limit associated with the aircraft and the course change associated with the segment and another segment, determine another specific bank angle value; and update the lateral trajectory profile to set the bank angle parameter to another specific bank angle value.

[0010] In another aspect, one or more processors are also configured to: after updating the lateral trajectory profile to unlock the tilt angle parameter and unlock the ground speed parameter, and based on the vertical trajectory profile associated with the flight plan, determine another specific ground speed value; and update the lateral trajectory profile to set the ground speed parameter to another specific ground speed value.

[0011] In another aspect, one or more processors are also configured to: determine a lateral distance threshold associated with the end waypoint of the flight segment, based on the fact that the flight segment with the determined lateral trajectory profile is active.

[0012] In another aspect, to determine the lateral distance threshold, one or more processors are configured to: identify a minimum roll angle value associated with the lateral trajectory profile based on the segment being active; identify an established ground speed value for the aircraft based on the segment being active; determine a maximum radius of transition based on the minimum roll angle value and the established ground speed value; and determine the lateral distance threshold based on the maximum radius and the heading change associated with said segment and another segment.

[0013] In one aspect, a non-transitory computer-readable medium storing a set of instructions, the set of instructions comprising: one or more instructions, when executed by one or more processors of an aircraft's FMS, causing the FMS to: determine that a segment of a lateral trajectory profile associated with the aircraft's flight plan is active; based on the determination that the segment of the lateral trajectory profile is active, determine a lateral distance threshold associated with the end waypoint of the segment; determine whether the lateral distance between the aircraft and the end waypoint satisfies the lateral distance threshold; and selectively perform one of the following operations: based on the determination that the lateral distance satisfies the lateral distance threshold, perform a first update to the lateral trajectory profile to lock the tilt angle parameter to a specific tilt angle value to which the aircraft's tilt angle has been set, or based on the determination that the lateral distance does not satisfy the lateral distance threshold, perform a second update to the lateral trajectory profile to set the tilt angle parameter to another tilt angle value.

[0014] In another aspect, when executed by one or more processors, the one or more instructions also cause FMS to: after performing the first update on the lateral trajectory profile, determine that the segment of the lateral trajectory profile is no longer active; and based on the fact that the segment of the lateral trajectory profile is no longer active, perform a third update on the lateral trajectory profile to unlock the tilt angle parameter.

[0015] In another aspect, when executed by one or more processors, the one or more instructions also cause the FMS to: after performing a first update on the lateral trajectory profile, determine whether the transition associated with the destination waypoint is active; and selectively perform one of the following operations: based on the determination that the transition is active, perform a third update on the lateral trajectory profile to lock the ground velocity parameters to a specific ground velocity value that the aircraft's ground velocity has been set, or based on the determination that the transition is not active, perform a fourth update on the lateral trajectory profile to set the ground velocity parameters to another specific ground velocity value.

[0016] On another front, one or more instructions that cause the FMS to perform a third update on the lateral trajectory profile result in the FMS: determining that the transition is active, determining that the segment is still active; and performing a third update on the lateral trajectory profile based on determining that the segment is still active.

[0017] In another aspect, one or more instructions that cause the FMS to perform a first update on the lateral trajectory profile cause the FMS to: based on the first update, cause the aircraft's bank angle to be locked at a specific bank angle value until the segment is no longer active; and wherein one or more instructions that cause the FMS to perform a third update on the lateral trajectory profile cause the FMS to: based on the third update, cause the aircraft's ground speed to be locked at a specific ground speed value until the segment is no longer active.

[0018] In another aspect, when executed by one or more processors, the one or more instructions also cause FMS to: after performing a third update on the lateral trajectory profile, determine that the segment of the lateral trajectory profile is no longer active; and based on the determination that the segment of the lateral trajectory profile is no longer active, perform a fifth update on the lateral trajectory profile to unlock the tilt angle parameter and unlock the ground speed parameter.

[0019] On another front, when executed by one or more processors, the one or more instructions also cause FMS to perform a sixth update on the lateral trajectory profile after the fifth update to set the tilt angle parameter to another specific tilt angle value.

[0020] On another front, when executed by one or more processors, the one or more instructions also cause FMS to perform a sixth update on the lateral trajectory profile after the fifth update to set the ground velocity parameter to another specific ground velocity value.

[0021] In another aspect, one or more instructions that cause the FMS to determine the lateral distance threshold cause the FMS to: determine the maximum radius of the transition associated with the end waypoint based on the minimum tilt angle value associated with the lateral trajectory profile and the specific ground velocity value for establishing the aircraft's ground velocity; and determine the lateral distance threshold based on the maximum radius.

[0022] In one aspect, a method includes: determining, by the FMS of an aircraft, whether the lateral distance between the aircraft and the end waypoint of the lateral trajectory profile meets a lateral distance threshold based on the fact that the segment is active; and selectively performing one of the following operations: first updating the lateral trajectory profile based on the determination that the lateral distance meets the lateral distance threshold to lock the tilt angle parameter to a specific tilt angle value, or second updating the lateral trajectory profile based on the determination that the lateral distance does not meet the lateral distance threshold to set the tilt angle parameter to another tilt angle value.

[0023] In another aspect, the method also includes: performing a third update on the lateral trajectory profile after the first update is performed and based on the fact that the segment that determined the lateral trajectory profile is no longer active, so as to cause the lateral trajectory profile to unlock the tilt angle parameter.

[0024] In another aspect, the method further includes: after performing a first update on the lateral trajectory profile, selectively performing one of the following operations: based on determining that the transition associated with the endpoint waypoint is active, performing a third update on the lateral trajectory profile to lock the ground velocity parameter to a specific ground velocity value, or based on determining that the transition associated with the endpoint waypoint is not active, performing a fourth update on the lateral trajectory profile to set the ground velocity parameter to another specific ground velocity value.

[0025] In another aspect, the method also includes performing a fifth update on the lateral trajectory profile after the third update is performed and the segment that determined the lateral trajectory profile is no longer active, in order to unlock the tilt angle parameter and unlock the ground speed parameter.

[0026] In one aspect, a system is configured to perform one or more operations described in one or more aspects herein.

[0027] In one aspect, an apparatus includes means for performing one or more operations described in one or more aspects herein.

[0028] In one aspect, a computer program product includes instructions or code for performing one or more operations described in one or more aspects herein.

[0029] The foregoing disclosure provides illustrations and descriptions, but is not intended to be exhaustive or to limit the embodiments described herein to their precise forms. Modifications and variations can be made based on the foregoing descriptions, or modifications and variations can be derived from the practice of the embodiments described herein.

[0030] The features, functions, and advantages already discussed can be implemented independently in various embodiments or combined in other embodiments, as can be seen in further details with reference to the following description and figures. Attached Figure Description

[0031] Figures 1A-1K This is a diagram of an example implementation related to the locking tilt angle parameter and the ground velocity parameter.

[0032] Figure 2 This is a diagram of an example environment in which the systems and / or methods described herein can be implemented.

[0033] Figure 3 This is a diagram of an example component of a device associated with locking tilt angle parameters and ground velocity parameters.

[0034] Figure 4 This is an example graph associated with dynamically calculated tilt angle parameters.

[0035] Figure 5A and Figure 5B This is a diagram of an example implementation related to determining the expected turning distance for a transition.

[0036] Figures 6A-6C This is a diagram of an example implementation related to the turning radius of the transition.

[0037] Figure 7 This is a flowchart of an example process associated with locking the tilt angle parameter and the ground velocity parameter. Detailed Implementation

[0038] The following detailed description of the exemplary embodiments is with reference to the accompanying drawings. The same reference numerals in different drawings may identify the same or similar elements.

[0039] The FMS (Flight Management System) calculates and updates the trajectory profile of the aircraft's flight plan. The goal of the FMS is to stabilize the aircraft's lateral trajectory during flight, thereby avoiding sudden navigational changes that could lead to cross-track errors. In many cases, transitions from one segment to another are indicated by the lateral trajectory profile of the flight plan, and the FMS calculates the turning radius of the transition as the aircraft crosses it (e.g., while flying along the path of the transition). The FMS determines the turning radius based on the aircraft's current ground speed and current bank angle. In some cases, changes in ground speed or bank angle cause a sudden change in the turning radius of the transition. Because the aircraft is crossing the transition when the turning radius changes abruptly, it may deviate from the transition's path. Therefore, the FMS, along with other guidance systems on the aircraft, often needs to induce corrective maneuvers to realign the aircraft with the transition's path. This increases the workload of the FMS and other guidance systems in calculating and implementing corrective maneuvers, and may increase the fuel consumption of the aircraft performing these maneuvers.

[0040] Some implementations described herein include the FMS (Flight Management System) of an aircraft. The FMS identifies a lateral trajectory profile associated with the aircraft's flight plan, indicating multiple segments between waypoints or other navigation points, and one or more transitions (e.g., from one segment to another). The lateral trajectory profile may also indicate bank angle parameters (e.g., associated with the aircraft's bank angle) and ground speed parameters (e.g., associated with the aircraft's ground speed), which the FMS uses to determine the turning radius of each of the one or more transitions.

[0041] In some implementations, the FMS determines that the segment of the lateral trajectory profile is active. That is, the FMS determines that the aircraft is currently traversing a segment indicated by the lateral trajectory profile. Therefore, the FMS determines whether the lateral distance between the aircraft and the endpoint waypoint associated with the segment meets (e.g., is less than or equal to) a lateral distance threshold. The lateral distance threshold could be, for example, the maximum distance from the endpoint waypoint associated with the maximum turning radius of the transition from this segment to another segment. When the FMS determines that the lateral distance threshold is not met, the FMS updates the lateral trajectory profile to set the lateral trajectory profile's bank angle parameter to a bank angle value dynamically calculated by the FMS. Alternatively, when the FMS determines that the lateral distance threshold is met, the FMS updates the lateral trajectory profile to lock the bank angle parameter to a specific bank angle value, such as an established bank angle value (e.g., the aircraft's bank angle is already set to that value). The bank angle parameter is then locked until the segment is no longer active.

[0042] Furthermore, after updating the lateral trajectory profile to lock the bank angle parameters, the FMS determines whether the transition is active (e.g., whether the aircraft is crossing a transition). When the FMS determines that the transition is not active, it updates the lateral trajectory profile to set the ground velocity parameters of the lateral trajectory profile to ground velocity values ​​dynamically calculated by the FMS. Alternatively, when the FMS determines that the transition is active, it updates the lateral trajectory profile to lock the ground velocity parameters to a specific ground velocity value, such as an established ground velocity value (e.g., the aircraft's ground velocity is already set to that value). The ground velocity parameters are then locked until the segment is no longer active.

[0043] Therefore, when both the bank angle and ground speed parameters are locked, the FMS determines the turning radius of the transition (e.g., based on the locked bank angle and ground speed parameters). Because the bank angle and ground speed parameters are locked until the segment is no longer active (e.g., until the aircraft passes the segment sequence point associated with the transition), the turning radius of the transition is fixed (e.g., does not deviate) when the segment is active. Furthermore, in some implementations, when the segment is active, the FMS causes the aircraft's bank angle to be locked at a specific bank angle value (e.g., as indicated by the locked bank angle parameters) and / or causes the aircraft's ground speed to be locked at a specific ground speed value (e.g., as indicated by the locked ground speed parameters) to ensure that the aircraft travels along the fixed turning radius of the transition.

[0044] In this way, the FMS prevents the turning radius of the transition from changing abruptly when the aircraft crosses it. Therefore, since the turning radius does not change abruptly, the aircraft is less likely to deviate from the transition path. Consequently, corrective maneuvers to realign the aircraft with the transition path are less likely to be needed. Thus, the workload of the FMS and other guidance systems on calculating and implementing any corrective maneuvers is reduced, and the aircraft's fuel efficiency is improved by performing fewer or no corrective maneuvers.

[0045] After a flight segment ceases to be active, the FMS unlocks the bank angle and ground speed parameters. At this point, the next flight segment is active, and the FMS iteratively performs at least some of the aforementioned operations. For example, starting from another flight segment, the FMS updates the lateral trajectory profile to lock and unlock the bank angle and ground speed parameters, thereby facilitating the determination of the corresponding turning radii for other transitions indicated by the lateral trajectory profile. Since the corresponding turning radii for other transitions are fixed, the aircraft is less likely to deviate from the corresponding paths of other transitions, and therefore may not require additional corrective maneuvers to realign the aircraft with the corresponding paths of other transitions. This further reduces the workload of the FMS and other guidance systems on the aircraft, and further improves the aircraft's fuel efficiency.

[0046] Figures 1A-1K This is a diagram of an example implementation 100 related to the locking tilt angle parameter and the ground velocity parameter. (See diagram for example.) Figures 1A-1K As shown, Example Implementation 100 includes equipment for an aircraft, including an FMS and an aircraft sensor system. The following will combine... Figure 2 and Figure 3 Describe these devices in more detail.

[0047] The Flight Management System (FMS) uses the aircraft's flight plan as input to perform one or more functions associated with the aircraft, such as navigation, fuel management, and / or performance optimization. The flight plan indicates waypoints and other navigation points along the route the aircraft will follow during flight. The flight plan also includes stick trajectory profiles, lateral trajectory profiles, and vertical trajectory profiles. A stick trajectory profile indicates a discontinuous and non-flyable lateral trajectory (e.g., indicating a straight line or "stick," and a simple turning arc between waypoints and other navigation points indicated by the flight plan). A lateral trajectory profile indicates a continuous and flyable lateral trajectory (e.g., based on a stick trajectory), which includes additional details related to turns and transitions between waypoints and other navigation points. For example, a lateral trajectory profile may indicate a transition from a first segment of the lateral trajectory profile to a second segment. The lateral trajectory profile may also indicate bank angle parameters (e.g., associated with the aircraft's bank angle) and ground speed parameters (e.g., associated with the aircraft's ground speed), which can be used (e.g., by the FMS) to determine the turning radius of each transition indicated by the lateral trajectory profile. The vertical trajectory profile indicates the altitude and ground speed associated with each waypoint and other navigation point indicated by the flight plan.

[0048] Therefore, in order to use the flight plan, the FMS can identify each of the stick trajectory profile, lateral trajectory profile, and vertical trajectory profile (e.g., as input to the FMS). Furthermore, the FMS can iteratively update the stick trajectory profile, lateral trajectory profile, and / or vertical trajectory profile throughout the flight (e.g., based on information provided in the flight plan (e.g., information indicating the aircraft's tilt angle) and / or information provided by the aircraft's sensor systems (e.g., information indicating the aircraft's ground velocity and / or information indicating the aircraft's orientation)). The information described herein... Figures 1A-1K The related operations are associated with FMS updating the lateral trajectory profile to lock the bank angle parameters and / or ground speed parameters, such as a fixed turning radius that can determine the transition from one segment to another (e.g., both indicated by the lateral trajectory profile).

[0049] In some implementations, such as Figure 1AAs shown, and by reference numeral 102, the FMS determines that a segment of the lateral trajectory profile is active. That is, the FMS can determine that the aircraft is currently traversing a segment indicated by the lateral trajectory profile. For example, the FMS can monitor the aircraft's orientation (e.g., based on information obtained from the aircraft's sensor systems) and can determine that a segment is active when the aircraft enters a defined airspace or path associated with the segment (e.g., as indicated by the lateral trajectory profile).

[0050] The lateral trajectory profile indicates the endpoint waypoint associated with a flight segment. That is, the lateral trajectory profile can indicate that the endpoint waypoint is the end of one flight segment and the beginning of another. Therefore, the lateral trajectory profile can also indicate a transition from one flight segment to another (e.g., its association with the endpoint waypoint). Segment sequence points may be associated with transitions, indicating the bearing along the transition where the aircraft stops traversing the segment and begins traversing another segment (e.g., the bearing where one segment ceases activity and another segment becomes active).

[0051] In some implementations, such as Figure 1B As shown, and by reference to numeral 104, the FMS determines a lateral distance threshold associated with the end waypoint of a segment (e.g., based on determining that the segment is active). The lateral distance threshold can be, for example, the maximum lateral distance from the end waypoint, which is associated with the maximum turning radius of the transition between this segment and another segment. That is, the lateral distance threshold can be the maximum expected turning distance used to ensure the transition has the maximum turning radius. The lateral distance threshold can be indicated in the following ways: in It is the horizontal distance threshold. It is the maximum turning radius during the transition. V It is the ground speed of the aircraft. It is the gravitational constant. It is the minimum permissible tilt angle of the aircraft (e.g., as indicated by the lateral trajectory profile), such as 8 degrees, and Indicates the change of course of an aircraft associated with the transition from one segment to another.

[0052] Therefore, the FMS can identify (e.g., based on information obtained from the aircraft's sensor systems) that the aircraft's ground speed has an established ground speed value (e.g., the aircraft's ground speed is actively set to an established ground speed value when determining the lateral distance threshold), and can identify the minimum bank angle value associated with the lateral trajectory profile (e.g., the aircraft's minimum bank angle, as indicated by the lateral trajectory profile or flight plan). The FMS can thus determine (e.g., based on the minimum bank angle value and the established ground speed value) the maximum radius of the transition. Therefore, the FMS can determine the lateral distance threshold based on the maximum radius and the heading changes associated with this segment and another segment.

[0053] In some implementations, such as Figure 1C As shown, and by referring to reference number 106, the FMS determines whether the lateral distance threshold is met. That is, the FMS can determine whether the lateral distance between the aircraft and the destination waypoint meets (e.g., is less than or equal to) the lateral distance threshold. In other words, the FMS can determine whether the lateral distance between the aircraft and the destination waypoint is less than or equal to... d max .

[0054] FMS can be based on the aircraft's location ( Figure 1C The bearings shown are designated as "aircraft bearings" (e.g., based on information obtained from the aircraft's sensor systems) and the bearings of the destination waypoints. Figure 1C The lateral distance threshold is determined by the bearing (e.g., based on information from flight plan instructions) shown in the diagram as “waypoint bearing”. For example, the FMS can determine the lateral distance between the aircraft and the destination waypoint based on their respective bearings (e.g., their respective lateral bearings), and then determine whether the lateral distance is less than or equal to a lateral distance threshold. In this way, the FMS can determine whether the lateral distance meets the lateral distance threshold, or alternatively, whether the lateral distance does not meet the lateral distance threshold. Based on the determination that the lateral distance threshold is met, the FMS can perform the procedures described herein with... Figure 1D One or more associated operations. Alternatively, based on the determination that the lateral distance threshold is not met, FMS can perform the operations described herein related to... Figure 1J One or more related operations.

[0055] In some implementations, such as Figure 1D As shown, and by referring to numeral 108, FMS performs updates on the lateral trajectory profile (e.g., based on determining that the lateral distance meets a lateral distance threshold, as discussed in this paper). Figure 1C(As described in reference numeral 106). The FMS can perform updates on the lateral trajectory profile to lock the bank angle parameters (e.g., lock them to a specific bank angle value). The specific bank angle value can be, for example, an established bank angle value (e.g., a specific bank angle value that has been set when the lateral trajectory profile is updated), which may have already been set by the FMS. The FMS can perform updates on the lateral trajectory profile to lock the bank angle parameters to the specific bank angle value until the segment is no longer active (e.g., thereby preventing updates to the bank angle parameters until the segment is no longer active).

[0056] Updating the lateral trajectory profile to lock the bank angle parameter to a specific bank angle value can cause the aircraft's bank angle to be locked at that specific bank angle value (e.g., as indicated by the locked bank angle parameter), for example, until the flight segment is no longer active. For example, updating the lateral trajectory profile can cause the FMS to set and maintain the aircraft's bank angle at a specific bank angle value (e.g., until the flight segment is no longer active).

[0057] In some implementations, such as Figure 1E As shown, and by reference numeral 110, the FMS determines that a transition associated with the destination waypoint and another segment is active (e.g., after updating the lateral trajectory profile to lock the inclination angle parameters). That is, the FMS can determine that the aircraft is traversing a transition. For example, the FMS can monitor the aircraft's bearing (e.g., based on information obtained from the aircraft's sensor systems) and can determine that the transition is active (e.g., as indicated by the lateral trajectory profile) when the aircraft enters the defined airspace or path associated with the transition. Therefore, the FMS can perform the functions described herein related to... Figure 1E and reference number 112 and / or with Figure 1F One or more operations associated with reference number 114.

[0058] Alternatively, in some implementations, the FMS determines that the transition is not active (or has not yet become active). That is, the FMS can determine that the aircraft is not traversing the transition. For example, the FMS can monitor the aircraft's orientation (e.g., based on information obtained from the aircraft's sensor systems) and can determine that the transition is not active if the aircraft is not within the defined airspace or path associated with the transition (e.g., as indicated by the lateral trajectory profile). Therefore, the FMS may not perform the actions described herein with... Figure 1E and reference number 112 and Figure 1D Instead of one or more operations associated with reference number 114, it can perform the operations described herein with Figure 1K One or more operations associated with reference number 124.

[0059] In some implementations, such as Figure 1EAs further shown, and by reference numeral 112, the FMS determines that a flight segment is active (or still active) (e.g., after updating the lateral trajectory profile to lock the inclination angle parameters). That is, the FMS can determine that the aircraft is traversing a portion of a transition associated with the flight segment and has not yet crossed the segment sequence points associated with that transition. For example, the FMS can monitor the aircraft's bearing (e.g., based on information obtained from the aircraft's sensor systems) and can determine that a flight segment is active when the aircraft is within the defined airspace or path associated with the flight segment (e.g., as indicated by the lateral trajectory profile) and has not yet crossed the segment sequence points.

[0060] Therefore, in some implementations, the FMS can determine that a transition is active and a flight segment is active (e.g., both the transition and the flight segment are active). For example, the FMS can determine that a transition is active and a flight segment is active when the aircraft enters a defined airspace or path associated with a transition and when the aircraft is within a defined airspace or path associated with a flight segment.

[0061] In some implementations, such as Figure 1F As shown, and by reference numeral 114, the FMS performs updates to the lateral trajectory profile (e.g., based on determining that a transition is active or determining that a flight segment is active, as described in this paper regarding...). Figure 1E (And as described with reference to figures 110 and 112). The FMS can perform updates on the lateral trajectory profile to lock the ground speed parameters (e.g., lock them to a specific ground speed value). The specific ground speed value can be, for example, an established ground speed value (e.g., a specific ground speed value that has been set when the lateral trajectory profile is updated), which can be set by the FMS. The FMS can perform updates to lock the ground speed parameters to the specific ground speed value until the segment is no longer active (e.g., thereby preventing updates to the ground speed parameters until the segment is no longer active).

[0062] In some implementations, updating the lateral trajectory profile to lock the ground speed parameter to a specific ground speed value causes the aircraft's ground speed to be locked at that specific ground speed value (e.g., as indicated by the locked ground speed parameter), for example, until the segment is no longer active. For example, updating the lateral trajectory profile may cause the FMS to set and maintain the aircraft's ground speed at a specific ground speed value (e.g., until the segment is no longer active).

[0063] Therefore, in some implementations, when both the bank angle parameter and the ground speed parameter are locked, the FMS determines the turning radius of the transition (e.g., based on the bank angle parameter and the ground speed parameter). Because the bank angle parameter and the ground speed parameter are locked until the segment is no longer active (e.g., until the aircraft passes the segment sequence point of the transition associated with that segment), the turning radius of the transition is fixed (e.g., does not deviate) when the segment is active. Furthermore, as described elsewhere herein, when the segment is active, the FMS can cause the aircraft's bank angle to be locked at a specific bank angle value (e.g., as indicated by the bank angle parameter) and / or cause the aircraft's ground speed to be locked at a specific ground speed value (e.g., as indicated by the ground speed parameter) to ensure that the aircraft travels along the fixed turning radius of the transition.

[0064] In some implementations, such as Figure 1G As shown, and by reference numeral 116, the FMS determines that a segment of the lateral trajectory profile is not active (or is no longer active) (e.g., after updating the lateral trajectory profile to lock the bank angle parameters and / or ground speed parameters). That is, the FMS can determine that the aircraft is not traversing (or no longer traversing) a segment and / or has traversed a segment sequence point associated with the transition. For example, the FMS can monitor the aircraft's bearing (e.g., based on information obtained from the aircraft's sensor systems) and can determine that a segment is not active when the aircraft is not within the defined airspace or path associated with the segment (e.g., as indicated by the lateral trajectory profile) and / or has traversed a segment sequence point. Therefore, the FMS can perform the functions described herein with... Figure 1H and Figure 1I One or more related operations.

[0065] In some implementations, such as Figure 1H As shown, and by referring to numeral 118, the FMS performs updates to the lateral trajectory profile (e.g., based on the fact that the segment for determining the lateral trajectory profile is not active, as discussed in this paper). Figure 1G (As described in reference numeral 116). FMS can perform updates on the lateral trajectory profile to unlock the tilt angle parameter. This allows the tilt angle parameter to be set to another specific tilt angle value (e.g., with respect to the values ​​described in this document). Figure 1J The method described is similar to that described above.

[0066] In some implementations, updating the lateral trajectory profile to unlock the tilt angle parameter causes the aircraft's tilt angle to stop being locked at a specific tilt angle value. For example, updating the lateral trajectory profile may cause the FMS to set the tilt angle to another specific tilt angle value.

[0067] In some implementations, such as Figure 1IAs shown, and by referring to numeral 120, the FMS performs updates to the lateral trajectory profile (e.g., based on the fact that the segment for determining the lateral trajectory profile is not active, as discussed in this paper). Figure 1G (As described in reference numeral 116). FMS can perform updates on the lateral trajectory profile to unlock the ground velocity parameters. This allows the ground velocity parameters to be set to another specific ground velocity value (e.g., with respect to the ground velocity parameters described in this document). Figure 1J The method described is similar to that described above.

[0068] In some implementations, updating the lateral trajectory profile to unlock the ground velocity parameters causes the aircraft's ground velocity to stop locking at a specific ground velocity value. For example, updating the lateral trajectory profile may cause the FMS to set the ground velocity to another specific ground velocity value.

[0069] In some implementations, such as Figure 1J As shown, and by referring to numeral 122, FMS performs updates on the lateral trajectory profile (e.g., based on determining that a lateral distance threshold is not met, as discussed in this paper). Figure 1C As described in reference numeral 106, and / or based on updating the lateral trajectory profile to unlock the tilt angle parameter, as described herein relative to... Figure 1H (As described in reference numeral 118). FMS can perform updates on the lateral trajectory profile to indicate whether the tilt angle parameters should be dynamically calculated.

[0070] In some implementations, updating the lateral trajectory profile to indicate the need for dynamic calculation of the bank angle parameters causes the FMS to dynamically calculate another specific bank angle value. For example, the FMS could determine another specific bank angle value based on roll constraints associated with the aircraft and heading changes associated with this segment and another segment (e.g., after the segment is no longer active), as described herein. Figure 4 Furthermore, the FMS can then update the lateral trajectory profile to set the tilt angle parameter to a different tilt angle value. Updating the lateral trajectory profile to set the tilt angle parameter to a different tilt angle value can cause the aircraft's tilt angle to be set to a different tilt angle value. For example, updating the lateral trajectory profile can cause the FMS to set the tilt angle to a different tilt angle value.

[0071] In some implementations, such as Figure 1K As shown, and by referring to numeral 124, FMS performs updates to the lateral trajectory profile (e.g., based on determining that the transition is not active, as discussed in this paper). Figure 1D As described in reference numeral 110, and / or based on updating the lateral trajectory profile to unlock ground velocity parameters, as per this document's description. Figure 1I(As described in reference numeral 120). The FMS can perform updates on the lateral trajectory profile to indicate the need for dynamically calculating ground velocity parameters.

[0072] In some implementations, updating the lateral trajectory profile to indicate the need for dynamic calculation of ground velocity parameters causes the FMS to dynamically calculate an additional specific ground velocity value. For example, the FMS might determine an additional specific ground velocity value based on the vertical trajectory profile associated with the flight plan. The FMS can then update the lateral trajectory profile to set the ground velocity parameters to this additional specific ground velocity value. Updating the lateral trajectory profile to set the ground velocity parameters to this additional specific ground velocity value can cause the aircraft's ground velocity to be set to this additional specific ground velocity value. For example, updating the lateral trajectory profile can cause the FMS to set the ground velocity to this additional specific ground velocity value.

[0073] As indicated above, Figures 1A-1K Provided as an example. Other examples may be related to... Figures 1A-1K The descriptions are different.

[0074] Figure 2 This is a diagram of an example environment 200 in which the systems and / or methods described herein can be implemented. (See diagram for example.) Figure 2 As shown, environment 200 may include aircraft 210, FMS 220, and / or aircraft sensor system 230. The devices in environment 200 may be interconnected via wired connections, wireless connections, or a combination of wired and wireless connections.

[0075] Aircraft 210 includes any suitable vehicle and / or equipment capable of flight. Aircraft 210 may include, for example, aircraft (e.g., jet aircraft, propeller aircraft, gliders, etc.), helicopters, unmanned or unmanned aerial vehicles (UAVs), drones, rocket ships, spacecraft, space shuttles, airships or blimps, and other examples of aerial vehicles and / or aerial equipment capable of flight.

[0076] FMS 220 includes one or more devices capable of receiving, generating, storing, transmitting, processing, and / or providing information, as described elsewhere herein. FMS 220 may include one or more devices, such as a Flight Management Computer (FMC), a Control Display Unit (CDU), and / or other devices that automate one or more of the flight planning, navigation, and operational tasks of aircraft 210. FMS 220 may be configured to generate, store, and / or update flight plans (e.g., including stick trajectory profiles, lateral trajectory profiles, and vertical trajectory profiles), as described elsewhere herein. FMS 220 may be configured to guide or otherwise control aircraft 210 according to the flight plan.

[0077] The aircraft sensor system 230 includes one or more devices capable of receiving, generating, storing, transmitting, processing, detecting, and / or providing information, as described elsewhere herein. The aircraft sensor system 230 may include one or more sensors or other devices configured to monitor, measure, and report information related to the operation, environment, and / or performance of the aircraft 210. For example, the aircraft sensor system 230 may include one or more sensors or other devices for detecting airspeed, ground speed, altitude, attitude, azimuth, roll angle, acceleration, one or more engine performance parameters, and / or other information associated with the aircraft. The aircraft sensor system 230 may be configured to sense or detect conditions or information and transmit indications of the detected conditions or information to the FMS 220 (e.g., in real-time or near real-time) using a wired or wireless communication interface.

[0078] Figure 2 The number and arrangement of devices and networks shown are provided as examples. In practice, there may be additional devices and / or networks, fewer devices and / or networks, different devices and / or networks, or [other arrangements]. Figure 2 The different arrangements of equipment and / or networks shown. Furthermore, Figure 2 The two or more devices shown can be implemented within a single device, or Figure 2 The single device described herein can be implemented as multiple distributed devices. Additionally, or alternatively, a group of devices in environment 200 (e.g., one or more devices) can perform one or more functions described as being performed by another group of devices in environment 200.

[0079] Figure 3 This is a diagram of example components of device 300 associated with lock-on tilt angle parameters and ground velocity parameters. Device 300 may correspond to aircraft 210, FMS 220, and / or aircraft sensor system 230. In some embodiments, aircraft 210, FMS 220, and / or aircraft sensor system 230 may include one or more devices 300 and / or one or more components of device 300. Figure 3 As shown, device 300 may include bus 310, processor 320, memory 330, input component 340, output component 350 and / or communication component 360.

[0080] Bus 310 may include one or more components that enable wired and / or wireless communication between components of device 300. Bus 310 can... Figure 3 Two or more components are coupled together (e.g., via operative coupling, communicative coupling, electronic coupling, and / or electrical coupling). For example, bus 310 may include electrical connections (e.g., wires, traces, and / or leads) and / or wireless buses. Processor 320 may include a central processing unit, graphics processing unit, microprocessor, controller, microcontroller, digital signal processor, field-programmable gate array, application-specific integrated circuit, and / or another type of processing unit. Processor 320 may be implemented in hardware, firmware, or a combination of hardware and software. In some embodiments, processor 320 may include one or more processors capable of being programmed to perform one or more operations or processes described elsewhere herein.

[0081] Memory 330 may include volatile and / or non-volatile memory. For example, memory 330 may include random access memory (RAM), read-only memory (ROM), hard disk drive, and / or another type of memory (e.g., flash memory, magnetic storage, and / or optical storage). Memory 330 may include internal memory (e.g., RAM, ROM, or hard disk drive) and / or removable memory (e.g., removable via a universal serial bus connection). Memory 330 may be a non-transitory computer-readable medium. Memory 330 may store information related to the operation of device 300, one or more instructions, and / or software (e.g., one or more software applications). In some embodiments, memory 330 may include one or more memories coupled (e.g., communication coupling) to one or more processors (e.g., processor 320), for example, via bus 310. The communication coupling between processor 320 and memory 330 enables processor 320 to read and / or process information stored in memory 330 and / or store information in memory 330.

[0082] Input component 340 enables device 300 to receive input, such as user input and / or sensed input. For example, input component 340 may include a touchscreen, keyboard, keypad, mouse, button, microphone, switch, sensor, GPS sensor, GNSS sensor, accelerometer, gyroscope, and / or actuator. Output component 350 enables device 300 to provide output (e.g., via a display, speaker, and / or LED). Communication component 360 enables device 300 to communicate with other devices via wired and / or wireless connections. For example, communication component 360 may include a receiver, transmitter, transceiver, modem, network interface card, and / or antenna.

[0083] Device 300 may perform one or more of the operations or processes described herein. For example, a non-transitory computer-readable medium (e.g., memory 330) may store a set of instructions (e.g., one or more instructions or code) for execution by processor 320. Processor 320 may execute the set of instructions to perform one or more of the operations or processes described herein. In some embodiments, execution of the set of instructions by one or more processors 320 causes one or more processors 320 and / or device 300 to perform one or more of the operations or processes described herein. In some embodiments, hardwired circuitry may be used in place of or in combination with instructions to perform one or more of the operations or processes described herein. Additionally, or alternatively, processor 320 may be configured to perform one or more of the operations or processes described herein. Therefore, the embodiments described herein are not limited to any particular combination of hardware circuitry and software.

[0084] Figure 3 The number and arrangement of the components shown are provided as an example. Figure 3 Compared to the components shown, device 300 may include additional components, fewer components, different components, or components arranged differently. Additionally, or alternatively, a set of components of device 300 (e.g., one or more components) may perform one or more functions described as being performed by another set of components of device 300.

[0085] Figure 4 This is an example graph 400 associated with the dynamically calculated tilt angle parameters. (See the article regarding...) Figure 1JAs described in reference numeral 122, the FMS can update the lateral trajectory profile of the flight plan to indicate the need for dynamic calculation of the bank angle parameters. This then causes the FMS to dynamically calculate a specific bank angle value 410, to which the bank angle parameters will be set. For example, the FMS can determine the specific bank angle value 410 based on the roll limits associated with the aircraft and the heading changes associated with the transition from one segment to another (e.g., as indicated by the lateral trajectory profile). The FMS can calculate the specific bank angle value 410 as half the angle associated with the heading change 420, between the minimum bank angle 430 and the maximum bank angle 440 of the roll limits. Therefore, as shown with respect to example diagram 400, when the angle associated with the heading change 420 is less than 16 degrees, the FMS can determine a specific bank angle value 410 as 8 degrees (e.g., when the minimum bank angle 430 of the roll limit is 8 degrees), when the angle associated with the heading change 420 is greater than or equal to 16 degrees and less than or equal to 50 degrees, the specific bank angle value 410 is determined as half of the angle associated with the heading change 420, or when the angle associated with the heading change 420 is greater than 50 degrees, the specific bank angle value 410 is determined as 25 degrees.

[0086] As indicated above, Figure 4 This is provided as an example. Other examples may be related to... Figure 4 The descriptions are different.

[0087] Figure 5A and Figure 5B These are figures for example implementations 500 and 510, respectively, which are associated with the aircraft's FMS determining the expected turning distance for the transition between one segment and another (e.g., as indicated by the lateral trajectory profile of the flight plan). Figures 5A-5B As shown, the aircraft 515 passes through segment 520, which has a destination waypoint 525. Segment 520 and destination waypoint 525 are associated with another segment 530 and a transition 535 from segment 520 to another segment 530.

[0088] Therefore, as Figure 5A As shown, the FMS of aircraft 515 determines the expected turning distance based on the heading changes associated with segment 520 and another segment 530. d To allow the transition 535 to have a turning radius R Expected turning distance d This can be indicated in the following ways: in R It is the turning radius of the transition 535, and Indicates the course change of aircraft 515 associated with the transition from segment 520 to another segment 530.

[0089] In some implementations, the turning radius of the transition can be maximized to ensure a smoother transition from segment 520 to another segment 530. For example, the FMS of aircraft 515 determines the maximum turning radius based on the ground speed of aircraft 515 and the minimum permissible bank angle of aircraft 515. R max Maximum turning radius during transition R max This can be indicated in the following ways: in V That is the ground speed of aircraft 515. It is the gravitational constant, and It is the minimum permissible tilt angle of the aircraft 515 (e.g., as indicated by the lateral trajectory profile), such as 8 degrees.

[0090] Therefore, as Figure 5B As shown, the FMS of aircraft 515 determines the maximum expected turning distance based on the heading changes associated with segment 520 and another segment 530. d max To allow the transition to have the maximum turning radius R max Maximum expected turning distance d max This can be indicated in the following ways: in It is the maximum turning radius of the transition 535, and Indicates the course change of aircraft 515 associated with the transition from segment 520 to another segment 530.

[0091] In some implementations, the lateral distance threshold (e.g., it is determined by the FMS, as described herein) is... Figure 1A (As stated in reference number 102) is the maximum expected turning distance. d max Therefore, when the lateral distance between aircraft 515 and the destination waypoint 525 meets (e.g., is less than or equal to) the lateral distance threshold (e.g., the maximum expected turning distance), d max When this is done, FMS can update the lateral trajectory profile to lock the tilt angle parameter, as described in this paper. Figure 1D As described in reference numeral 108, such as enabling the transition to have a maximum turning radius. R max .

[0092] As indicated above, Figures 5A-5B Provided as an example. Other examples may be related to... Figures 5A-5B The descriptions are different.

[0093] Figure 6A , Figure 6B and Figure 6C The figures are examples 600, 610, and 620, respectively, which are associated with the aircraft's ground speed and the turning radius of the transition between one segment and another (e.g., as indicated by the lateral trajectory profile of the flight plan). Figures 6A-6C As shown, vehicle 625 is associated with segment 630, which has a destination waypoint 635. Segment 630 and destination waypoint 635 are associated with another segment 640 and a transition 645 between segment 630 and the other segment 640. Segment sequence point 650 is associated with transition 645.

[0094] like Figure 6A As shown, at the first moment, aircraft 625 has a ground velocity value v 1 The ground speed is used to traverse segment 630. Since aircraft 625 has not yet traversed transition 645, the FMS of aircraft 625 uses the ground speed value. v 1 To determine the turning radius of transition 645. r 1 At the second moment after the first moment, the ground velocity value changed from... v 1 Descending to v 2 Therefore, since aircraft 625 has not yet crossed transition 645, the FMS of aircraft 625 uses ground velocity values. v 2 To determine the turning radius of transition 645. r 2 Furthermore, since the ground speed of aircraft 625 has decreased, r 2 Less than r 1 .

[0095] like Figure 6B As shown, at the third moment, segment 630 is still active, and aircraft 625 is moving at a ground speed value. v 3 The ground speed passes through transition 645. Since both segment 630 and transition 645 are active, the FMS of aircraft 625 uses a locked ground speed value v. L(For example, as indicated by the ground velocity parameters locked in the lateral trajectory profile) to determine the turning radius of transition 645. r 3 It is equal to the locked turning radius. r L At the fourth moment, following the third moment, the ground velocity value changed from... v 3 Descending to v 4 Therefore, since both segment 630 and transition 645 remain active, the FMS continues to use the locked ground speed value v. L (For example, as indicated by the ground velocity parameters locked in the lateral trajectory profile) to determine the turning radius of transition 645. r 4 It is equal to the locked turning radius. r L Therefore, regardless of how the ground speed of aircraft 625 changes, the turning radius of transition 645 will not change.

[0096] like Figure 6C As shown, at the fifth moment, segment 630 is no longer active, and aircraft 625 has a ground speed value v 5 The ground speed passes through transition 645. Since segment 630 is no longer active, the FMS of aircraft 625 does not update the turning radius of transition 645. r L (For example, because aircraft 625 is about to or will pass through segment 640). At the sixth moment after the fifth moment, the ground speed value changes from... v 5 Reduce to v 6 Therefore, since transition 645 remains active and segment 630 remains inactive, FMS continues not to update the turning radius of transition 645. r L (For example, as aircraft 625 is about to or will pass through segment 640). Therefore, regardless of how the ground speed of aircraft 625 changes, the turning radius of transition 645 will not change.

[0097] As indicated above, Figures 6A-6C Provided as an example. Other examples may be related to... Figures 6A-6C The descriptions are different.

[0098] Figure 7 This is a flowchart of an example process 700 associated with locking tilt angle parameters and ground velocity parameters. In some implementations, Figure 7One or more operations are performed by the FMS (e.g., FMS 220) of the aircraft (e.g., aircraft 210). In some implementations, Figure 7 One or more operations are performed by another device or group of devices that are separate from or include the FMS (e.g., the aircraft's aircraft sensor system (e.g., aircraft sensor system 230)). Additionally, or alternatively, Figure 7 One or more operations can be performed by one or more components of the device 300 (e.g., processor 320, memory 330, input component 340, output component 350 and / or communication component 360).

[0099] like Figure 7 As shown, process 700 includes determining whether a segment of the lateral trajectory profile associated with the aircraft's flight plan is active (operation 710). For example, the FMS can determine whether a segment of the lateral contour associated with the aircraft's flight plan is active (e.g., in relation to the information described herein). Figure 1A (Similar to the manner described with reference to figure 102). When the FMS determines that the segment is active, process 700 may then include performing operation 720. Alternatively, when the FMS determines that the segment is not active, process 700 may then include performing operations 740 and 780 (and may not include performing any other operations described herein). Thus, the FMS may selectively perform either operation 720 (e.g., based on determining that the segment is active) or operations 740 and 780 (e.g., based on determining that the segment is not active).

[0100] like Figure 7 As shown, process 700 includes determining whether a lateral distance threshold is met (operation 720). For example, the FMS can determine whether the lateral distance between the aircraft and the end waypoint of the segment meets a lateral distance threshold associated with the end waypoint (e.g., in relation to the lateral distance mentioned in this document). Figure 1C (Similar to the manner described in reference numeral 106). When the FMS determines that the lateral distance meets a lateral distance threshold, process 700 may then include performing operation 730. Alternatively, when the FMS determines that the lateral distance does not meet the lateral distance threshold, process 700 may then include performing operation 740 (and may not include performing any other operations described herein). Thus, the FMS can selectively perform either operation 730 (e.g., based on determining that the lateral distance meets the lateral distance threshold) or operation 740 (e.g., based on determining that the lateral distance does not meet the lateral distance threshold).

[0101] like Figure 7As shown, process 700 includes performing an update on the lateral trajectory profile to lock the tilt angle parameter (operation 730). For example, FMS can perform an update on the lateral trajectory profile (e.g., a first update) to lock the tilt angle parameter to a specific tilt angle value (e.g., in accordance with the values ​​described herein). Figure 1D (Similar to the manner described in reference numeral 108). Process 700 may then include performing operation 750.

[0102] like Figure 7 As shown, process 700 includes updating the lateral trajectory profile to cause the lateral trajectory profile to indicate that the tilt angle parameter should be dynamically calculated (operation 740). For example, FMS can perform an update on the lateral trajectory profile (e.g., a second update) to cause the lateral trajectory profile to indicate that the tilt angle parameter should be dynamically calculated (e.g., in accordance with the description in this document regarding...). Figure 1J (Similar to the method described in reference numeral 122). This can cause the FMS to dynamically calculate another specific tilt angle value and perform an update on the lateral trajectory profile to set the tilt angle parameter to another specific tilt angle value.

[0103] like Figure 7 As shown, process 700 includes determining whether a transition associated with a destination waypoint is active (operation 750). For example, the FMS can determine whether a transition associated with a destination waypoint is active (e.g., in relation to the transitions described herein). Figure 1E (Similar to the manner described in reference numeral 110). When the FMS determines that the transition is active, process 700 may then include performing operation 750 (or performing operation 770 without performing operation 750). Alternatively, when the FMS determines that the transition is not active, process 700 may then include performing operation 780 (and may not include performing any other operations described herein). Thus, the FMS can selectively perform one of operation 750 (or operation 770) (e.g., based on determining that the transition is active) or operation 780 (e.g., based on determining that the transition is not active).

[0104] like Figure 7 As shown, process 700 includes determining whether the flight segment is (still) active (operation 760). For example, the FMS can determine whether the flight segment is (still) active (e.g., in accordance with the information provided herein). Figure 1E and reference number 112 and Figure 1G(Similar to the manner described in reference numeral 116). When the FMS determines that the segment is (still) active, process 700 may then include performing operation 770. Alternatively, when the FMS determines that the segment is not active (or is no longer active), process 700 may then include performing operation 790 (and may not include performing any other operations described herein). Thus, the FMS may selectively perform either operation 770 (e.g., based on determining that the segment is (still) active) or operation 790 (e.g., based on determining that the segment is not active).

[0105] like Figure 7 As shown, process 700 includes updating the lateral trajectory profile to lock the ground velocity parameters to a specific ground velocity value (operation 770). For example, the FMS can perform an update on the lateral trajectory (e.g., a third update) to lock the ground velocity parameters to a specific ground velocity value (e.g., with respect to the ground velocity parameters described herein). Figure 1F (Similar to the method described in reference number 114).

[0106] like Figure 7 As shown, process 700 includes updating the lateral trajectory profile to cause the lateral trajectory profile to indicate that ground velocity parameters should be dynamically calculated (operation 780). For example, the FMS can perform an update on the lateral trajectory profile (e.g., a fourth update) to cause the lateral trajectory profile to indicate that ground velocity parameters should be dynamically calculated (e.g., in accordance with the description in this document regarding...). Figure 1K (Similar to the method described in reference numeral 124). This can cause the FMS to dynamically calculate another specific ground velocity value and perform an update on the lateral trajectory profile to set the ground velocity parameter to another specific tilt angle value.

[0107] like Figure 7 As shown, process 700 includes updating the lateral trajectory profile to cause the lateral trajectory profile to unlock specific tilt angle parameters and unlock specific ground velocity parameters (operation 790). For example, the FMS can perform an update on the lateral trajectory profile (e.g., a fifth update) to cause the lateral trajectory profile to unlock specific tilt angle parameters and unlock specific ground velocity parameters (e.g., in accordance with the descriptions herein). Figure 1H And reference number 118 and Figure 1I (Similar to the method described in reference number 120).

[0108] although Figure 7 Example operations of process 700 are shown, but in some embodiments, process 700 includes additional operations, fewer operations, different operations, or operations arranged differently (with...). Figure 7 Compared to those operations described in [the document]. Additionally, or alternatively, two or more operations of process 700 may be performed in parallel.

[0109] In some implementations, process 700 or one or more parts of process 700 may be executed iteratively. In this way, the FMS may perform one or more additional updates to the lateral trajectory profile (e.g., a sixth update, a seventh update, etc.) to lock and unlock inclination angle parameters and ground speed parameters associated with other segments and transitions of the lateral trajectory profile.

[0110] In addition, this application includes configurations based on the following examples.

[0111] Example 1. A non-transitory computer-readable medium (330) storing a set of instructions, said set of instructions comprising: One or more instructions, when executed by one or more processors (320) of the flight management system (FMS) (220) of the aircraft (210), cause the FMS (220) to: The segment of flight that determines the lateral trajectory profile associated with the flight plan of the aircraft (210) is active; Based on the fact that the segment is active according to the determination of the lateral trajectory profile, a lateral distance threshold associated with the end waypoint of the segment is determined; Determine whether the lateral distance between the aircraft (210) and the destination waypoint meets the lateral distance threshold; and Selectively perform one of the following operations: Based on the determination that the lateral distance meets the lateral distance threshold, the lateral trajectory profile is updated for the first time to lock the tilt angle parameter to a specific tilt angle value that has been set for the aircraft (210), or Based on the determination that the lateral distance does not meet the lateral distance threshold, the lateral trajectory profile is updated a second time to set the tilt angle parameter to another tilt angle value.

[0112] Example 2. A non-transitory computer-readable medium (330) according to Example 1, wherein the one or more instructions, when executed by the one or more processors (320), also cause the FMS (220): After performing the first update on the lateral trajectory profile, it is determined that the segment of the lateral trajectory profile is no longer active; and Based on the determination that the segment of the lateral trajectory profile is no longer active, a third update is performed on the lateral trajectory profile to unlock the tilt angle parameter.

[0113] Example 3. A non-transitory computer-readable medium (330) according to Example 1, wherein, when executed by the one or more processors (320), the one or more instructions also cause the FMS (220): After performing the first update on the lateral trajectory profile, determine whether the transition associated with the endpoint waypoint is active; and Selectively perform one of the following operations: Based on the determination that the transition is active, the lateral trajectory profile is updated a third time to lock the ground velocity parameters to a specific ground velocity value that has been set for the aircraft (210), or Based on the determination that the transition is not active, the lateral trajectory profile is updated a fourth time to set the ground velocity parameter to another specific ground velocity value.

[0114] Example 4. A non-transitory computer-readable medium (330) according to Example 3, wherein the one or more instructions that cause the FMS (220) to perform the third update on the lateral trajectory profile cause the FMS (220) to: Based on the determination that the transition is active, it is determined that the flight segment remains active; and Based on the determination that the flight segment is still active, the third update is performed on the lateral trajectory profile.

[0115] Example 5. A non-transitory computer-readable medium (330) according to Example 3. The one or more instructions that cause the FMS (220) to perform the first update on the lateral trajectory contour result in the FMS (220): Based on the execution of the first update, the tilt angle of the aircraft (210) is locked at the specific tilt angle value until the flight segment is no longer active; and Among them, the one or more instructions that cause the FMS (220) to perform the third update on the lateral trajectory contour cause the FMS (200): Based on the execution of the third update, the ground speed of the aircraft (210) is locked at the specific ground speed value until the flight segment is no longer active.

[0116] Example 6. A non-transitory computer-readable medium (330) according to Example 3, wherein, when executed by the one or more processors (320), the one or more instructions also cause the FMS (220): After performing the third update on the lateral trajectory profile, it is determined that the segment of the lateral trajectory profile is no longer active; and Based on the determination that the segment of the lateral trajectory profile is no longer active, a fifth update is performed on the lateral trajectory profile to unlock the tilt angle parameter and the ground speed parameter.

[0117] Example 7. A non-transitory computer-readable medium (330) according to Example 6, wherein, when executed by the one or more processors (320), the one or more instructions also cause the FMS (220): After the fifth update is performed on the lateral trajectory profile, a sixth update is performed on the lateral trajectory profile to set the tilt angle parameter to another specific tilt angle value.

[0118] Example 8. A non-transitory computer-readable medium (330) according to Example 6, wherein, when executed by the one or more processors (320), the one or more instructions also cause the FMS (220): After the fifth update is performed on the lateral trajectory profile, a sixth update is performed on the lateral trajectory profile to set the ground velocity parameter to another specific ground velocity value.

[0119] Example 9. A non-transitory computer-readable medium (330) according to Example 1, wherein the one or more instructions that cause the FMS (220) to determine the lateral distance threshold cause the FMS (220) to: Based on the minimum tilt angle value associated with the lateral trajectory profile and a specific ground velocity value for establishing the ground velocity of the aircraft (210), the maximum radius of the transition associated with the endpoint waypoint is determined; and The lateral distance threshold is determined based on the maximum radius.

[0120] Example 10. A method comprising: The flight management system (FMS) (220) of the aircraft (210) determines whether the lateral distance between the aircraft (210) and the end waypoint of the flight segment meets a lateral distance threshold based on whether the segment with the defined lateral trajectory profile is active; and Selectively perform one of the following operations: Based on the determination that the lateral distance meets the lateral distance threshold, the lateral trajectory contour is updated for the first time to lock the tilt angle parameter to a specific tilt angle value, or Based on the determination that the lateral distance does not meet the lateral distance threshold, the lateral trajectory profile is updated a second time to set the tilt angle parameter to another tilt angle value.

[0121] Example 11. The method according to Example 10 further includes: After the first update is performed on the lateral trajectory profile, and based on the determination that the segment of the lateral trajectory profile is no longer active, a third update is performed on the lateral trajectory profile to cause the lateral trajectory profile to unlock the tilt angle parameter.

[0122] Example 12. The method according to Example 10 further includes: After performing the first update on the lateral trajectory profile, one of the following operations may be performed selectively: Based on the determination that the transition associated with the endpoint waypoint is active, the lateral trajectory profile is updated a third time to lock the ground velocity parameters to a specific ground velocity value, or Based on the determination that the transition associated with the endpoint waypoint is not active, the lateral trajectory profile is updated a fourth time to set the ground velocity parameter to another specific ground velocity value.

[0123] Example 13. The method according to Example 12 further includes: After the third update is performed on the lateral trajectory profile, and based on the determination that the segment of the lateral trajectory profile is no longer active, a fifth update is performed on the lateral trajectory profile to unlock the tilt angle parameter and the ground speed parameter.

[0124] As used herein, the term "component" is intended to be interpreted broadly as hardware, firmware, and / or a combination of hardware and software. It will be apparent that the systems and / or methods described herein can be implemented in various forms of hardware, firmware, or combinations of hardware and software. The actual dedicated control hardware or software code used to implement these systems and / or methods does not limit the implementations described herein. Therefore, the operation and behavior of the systems and / or methods are described herein without reference to specific software code—it is understood that software and hardware can be designed to implement the systems and / or methods based on the descriptions herein.

[0125] As used in this article, depending on the context, satisfying the threshold can mean that the value is greater than the threshold, greater than or equal to the threshold, less than the threshold, less than or equal to the threshold, equal to the threshold, not equal to the threshold, etc.

[0126] As used herein, “selectively” performing an operation means performing the operation or refraining from performing the operation. For example, selectively performing an operation based on whether a condition is met means performing the operation if the condition is met, and not performing the operation if the condition is not met (and vice versa). Therefore, selectively performing an operation may include determining whether to perform the operation, and then performing the operation or refraining from performing the operation based on that determination.

[0127] Although specific combinations of features are described in the claims and / or the specification, these combinations are not intended to limit the embodiments described herein. In fact, many of these features can be combined in ways not specifically stated in the claims and / or described in the specification. While each dependent claim listed herein may depend directly on only one claim, this specification includes each dependent claim in combination with each other claim in the group of claims. As used herein, the phrase “at least one” in the list of denotating items refers to any combination of these items (including a single member). For example, “at least one of a, b, or c” is intended to cover a, b, c, ab, ac, bc, and abc, and any combination with multiples of the same item.

[0128] When the term "a component" or "one or more components (or another element, such as "a processor" or "one or more processors") (within a single claim or across multiple claims) is described or claimed to perform or be configured to perform multiple operations, this language is intended to broadly encompass a wide range of architectures and contexts. For example, unless explicitly required otherwise (e.g., by using "first component" and "second component" or other language distinguishing components in a claim), this language is intended to cover a single component performing or configured to perform all operations, a group of components collectively performing or configured to perform all operations, a first component performing or configured to perform a first operation and a second component performing or configured to perform a second operation, or any combination of components performing or configured to perform these operations. For example, when a claim takes the form "one or more components are configured to: perform X; perform Y; and perform Z," the claim should be interpreted as meaning "one or more components are configured to perform X; one or more (possibly different) components are configured to perform Y; and one or more (possibly different) components are configured to perform Z." Unless explicitly stated otherwise, no element, action, or instruction used herein should be construed as critical or necessary. Furthermore, as used herein, “a” and “an” are intended to include one or more items and may be used interchangeably with “one or more.” Additionally, as used herein, “the” is intended to include one or more items referenced with respect to “the” and may be used interchangeably with “one or more.” Furthermore, as used herein, the term “set” is intended to include one or more items (e.g., related items, unrelated items, or a combination of related and unrelated items) and may be used interchangeably with “one or more.” Where only one item is intended, the phrase “only one” or similar language is used. Furthermore, as used herein, the term “has, have, having, etc.” is intended to be an open-ended term. Additionally, unless otherwise explicitly stated, the phrase “based on” is intended to mean “at least partially based on.” Furthermore, as used herein, the term “or” is intended to be inclusive when used in a series and can be used interchangeably with “and / or” unless otherwise explicitly stated (e.g., if used in conjunction with “any” or “only one of them)”).

Claims

1. A flight management system (FMS) (220) for an aircraft (210), comprising: One or more memory units (330); and One or more processors (320) communicatively coupled to the one or more memories (330), the one or more processors (320) being configured to: The segment of flight that determines the lateral trajectory profile associated with the flight plan of the aircraft (210) is active; Based on the fact that the segment of the flight path is active, the lateral distance between the aircraft (210) and the waypoint associated with the flight path is determined to meet the lateral distance threshold. Based on the determination that the lateral distance meets the lateral distance threshold, the lateral trajectory profile is updated to lock the tilt angle parameter to a specific tilt angle value; The transition associated with another segment of the endpoint waypoint and the lateral trajectory profile is determined to be active, and the segment is active; and Based on the determination that the transition is active and the flight segment is active, the lateral trajectory profile is updated to lock the ground speed parameters to a specific ground speed value.

2. The FMS (220) according to claim 1, wherein the one or more processors (320) are further configured to: Based on the tilt angle parameter and the ground speed parameter, the turning radius of the transition is determined, and the turning radius will be fixed until the segment is no longer active.

3. The FMS (220) according to claim 1, wherein the one or more processors (320) are further configured to: The flight segment whose lateral trajectory profile is determined is no longer active; and If the segment of the flight path is determined to be no longer active based on the determination of the lateral trajectory profile, the lateral trajectory profile is updated to unlock the tilt angle parameter and the ground speed parameter.

4. The FMS (220) according to claim 3, wherein the one or more processors (320) are further configured to: After updating the lateral trajectory profile to unlock the tilt angle parameter and the ground velocity parameter, and based on the roll limit associated with the aircraft (210) and the heading change associated with the segment and another segment, another specific tilt angle value is determined; and The lateral trajectory profile is updated to set the tilt angle parameter to another specific tilt angle value.

5. The FMS (220) according to claim 3, wherein the one or more processors (320) are further configured to: After performing the update on the lateral trajectory profile to unlock the tilt angle parameter and the ground velocity parameter, and based on the vertical trajectory profile associated with the flight plan, another specific ground velocity value is determined; and The lateral trajectory profile is updated to set the ground velocity parameter to another specific ground velocity value.

6. The FMS (220) according to claim 1, wherein, The one or more processors (320) are also configured to: Based on the determination that the segment of the lateral trajectory profile is active, a lateral distance threshold associated with the end waypoint of the segment is determined.

7. The FMS (220) according to claim 6, wherein, To determine the lateral distance threshold, the one or more processors (320) are configured to: Based on the determination that the flight segment of the lateral trajectory profile is active, the minimum tilt angle value associated with the lateral trajectory profile is identified; Based on the fact that the segment of flight, whose lateral trajectory profile is determined, is active, the ground velocity of the aircraft (210) is identified as having an established ground velocity value; Based on the minimum tilt angle value and the established ground velocity value, the maximum radius of the transition is determined; and The lateral distance threshold is determined based on the maximum radius and the heading changes associated with the segment and another segment.

8. A non-transitory computer-readable medium (330) storing a set of instructions, said set of instructions comprising: One or more instructions, when executed by one or more processors (320) of the flight management system (FMS) (220) of the aircraft (210), cause the FMS (220) to: The segment of flight that determines the lateral trajectory profile associated with the flight plan of the aircraft (210) is active; Based on the fact that the segment is active according to the determination of the lateral trajectory profile, a lateral distance threshold associated with the end waypoint of the segment is determined; Determine whether the lateral distance between the aircraft (210) and the destination waypoint meets the lateral distance threshold; and Selectively perform one of the following operations: Based on the determination that the lateral distance meets the lateral distance threshold, the lateral trajectory profile is updated for the first time to lock the tilt angle parameter to a specific tilt angle value that has been set for the aircraft (210), or Based on the determination that the lateral distance does not meet the lateral distance threshold, the lateral trajectory profile is updated a second time to set the tilt angle parameter to another tilt angle value.

9. The non-transitory computer-readable medium (330) according to claim 8, wherein, When the one or more instructions are executed by the one or more processors (320), they also cause the FMS (220): After performing the first update on the lateral trajectory profile, it is determined that the segment of the lateral trajectory profile is no longer active; and Based on the determination that the segment of the lateral trajectory profile is no longer active, a third update is performed on the lateral trajectory profile to unlock the tilt angle parameter.

10. The non-transitory computer-readable medium (330) according to claim 8, wherein, when executed by the one or more processors (320), the one or more instructions further cause the FMS (220): After performing the first update on the lateral trajectory profile, determine whether the transition associated with the endpoint waypoint is active; and Selectively perform one of the following operations: Based on the determination that the transition is active, the lateral trajectory profile is updated a third time to lock the ground velocity parameters to a specific ground velocity value that has been set for the aircraft (210), or Based on the determination that the transition is not active, the lateral trajectory profile is updated a fourth time to set the ground velocity parameter to another specific ground velocity value.

Images