Control devices and aircraft with pitch and flight path-based operating modes for flight direction indicators

Abstract

A flight system comprising: a display unit configured to display an image; a control device communicatively connected to the display unit and configured to control the display unit to display the image in a control device operating mode for launching and a control device operating mode for flying, the control device further configured to: Receiving signals indicating an aircraft attitude, a target attitude and a flight path of an aircraft; Creating a marker in the image in the launch mode based on an attitude difference between the aircraft attitude and the target attitude; Creating the marker in the image in the flight mode based on the flight path; and Generating a signal that causes the display unit to display the image.

Description

TECHNICAL FIELD

[0001] The technical field relates generally to a flight control system and relates more particularly to flight systems, control devices and aircraft having pitch-based flight control in an operating condition for takeoff and trajectory-based flight control in an operating condition for flight.

[0002] During takeoff, the pilot must precisely turn or pitch the aircraft to a desired pitch angle without over- or under-pitching. Precise pitching results in optimal performance when hitting a takeoff zone and promotes passenger and crew safety.

[0003] US 2006 / 0 220 921 A1 describes methods and systems for assisting aircraft pilots during a maneuver that causes an increase in the aircraft's attitude. The system comprises a set of information sources that determine at least a current attitude of the aircraft, a first means for transmitting a first attitude value, a second means for determining an attitude deviation by subtracting the first attitude value from the current attitude, and a head-up display capable of presenting on a screen, superimposed on the surroundings, at least a horizon line and a first indication means indicating this attitude deviation.

[0004] US 2012 / 0 299 753 A1 describes a system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, flight, descent, landing) to pilots in response to situations, without relying on measured air data. This information is presented intuitively and conveniently on the primary flight display, when and where it is needed. The displayed information changes dynamically in response to aircraft parameters.

[0005] US 2012 / 0 316 706 A1 describes a Climb-Optimized Takeoff System, whereby an improvement is achieved by allowing the aircraft to transition to an optimized pitch attitude during and after takeoff, while ensuring that the minimum required takeoff climb gradients and the geometric constraints of the aircraft are taken into account.

[0006] US 2015 / 0 211 883 A1 describes an apparatus and method for displaying a predicted image for a rotocraft flight taking into account data related to a selected flight procedure and a current image.

[0007] A flight guide is a device used in aviation that produces images on a flight display unit to assist the pilot in flying the aircraft through various operational states of flight. Pilots typically position a flight path marker or a pitch marker on a flight guide to achieve a desired pitch during takeoff. However, flight path markers are based on the aircraft's flight path. The aircraft's flight path is decoupled from the pitch-based pitch task, thereby allowing room for improvement in takeoff performance with flight path-based flight guides. Pitch-based flight guides are superior to flight path-based flight guides for takeoff performance, but pitch-based flight guides provide suboptimal guidance once the aircraft is in flight.

[0008] It is advantageous to provide flight systems, control devices, and aircraft that provide improved flight guidance for pitch and trajectory-based tasks during flight. Additionally, other advantageous features and characteristics will become apparent from the following summary and detailed description and the appended claims, taken in conjunction with the accompanying drawings and this technical background.

[0009] Various non-limiting embodiments of flight systems, flight system control devices, and aircraft are disclosed herein.

[0010] In a first non-limiting embodiment, a flight system includes, but is not limited to, a display unit and a controller. The display unit is configured to display an image. The controller is communicatively coupled to the display unit and configured to control the display unit to display the image from the controller in a takeoff operating mode and a flight operating mode. The controller is further configured to receive signals indicative of an aircraft attitude, a target attitude, and a flight path of the aircraft, generate a marker in the image during the takeoff operating mode based on an attitude difference between the aircraft attitude and a target attitude, generate the marker in the image based on the flight path during the flight operating mode, and generate a signal that causes the display unit to display the image.

[0011] In a second non-limiting embodiment, a control device for a flight system includes, but is not limited to, a processor and a memory unit. The memory unit is operatively coupled to the processor and contains instructions. The instructions and the processor cooperate to configure the control device to control a display unit to display an image in a launch mode of the control device and in a flight mode of the control device. The instructions and the processor further cooperate to configure the control device to receive signals indicative of an attitude of the aircraft, a target attitude, and a flight path of the aircraft. The instructions and the processor further cooperate to determine, based on an attitude difference between the aircraft attitude and the target attitude, a pitch roll, orIndicates pitch attitude, generates a marker in the image, and generates a signal that causes the display unit to display the image. A third non-limiting embodiment includes, but is not limited to, an aircraft control handle, a display unit, and a control device. The aircraft control handle is configured to receive steering movements for adjusting an attitude of the aircraft. The display unit is configured to display an image. The control device is communicatively coupled to the display unit and is configured to control the display unit to display the image in a takeoff control device operating mode and in a flight control device operating mode. The control device is further configured to receive signals indicative of an attitude of the aircraft, a target attitude, and a flight path of the aircraft.The control device is further configured to generate a marker in the image based on a position difference between the attitude of the aircraft and the target attitude in the takeoff operating state, generate the marker in the image based on the flight path in flight operation, and generate a signal that causes the display unit to display the image. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Advantages of the present embodiments will be appreciated as the embodiments become more clearly understood by reference to the following detailed description when taken in conjunction with the accompanying drawings. Fig. 1 is a simplified diagram showing a non-limiting embodiment of an aircraft in accordance with the teachings of the present disclosure; Fig. 2 is a simplified block diagram illustrating a non-limiting embodiment of a flight system of the aircraft as shown in Fig. 1 shows; Fig. 3, Fig. 4, and Fig. 5 are representations of images taken by the flight system Fig. 2; and Fig. 6 is a flowchart illustrating one non-limiting embodiment of a method for providing guidance to a pilot by a flight director during a takeoff procedure in accordance with the teachings of the present disclosure. DETAILED DESCRIPTION

[0013] The following detailed description is merely exemplary in nature and is not intended to limit the invention and its applications. Furthermore, there is no intention to be bound by any theory presented in the foregoing background or the following detailed description.

[0014] Various non-limiting embodiments of flight systems and aircraft are presented. In general, the disclosure herein describes a flight guidance system for use during a takeoff phase of flight. During takeoff, the pilot must accurately pitch or turn the aircraft to a target pitch without under- or over-pitching. The flight guidance system provides guidance to solve this pitch-based task and achieve a smooth transition to a deployment of trajectory-based guidance using a single set of display units.

[0015] During takeoff, the flight guidance system will provide guidance that represents the difference between the target pitch (θTarget) and the aircraft's pitch (θ). The error, or deviation, from the pitch to the target pitch, θ-θTarget, is represented in the drawings as the angular distance from the flight path / pitch marker to the flight direction indicator. A flight direction indicator is placed at a fixed location on the pitch scale of the display system, and the flight path / pitch marker is placed at a relative vertical distance based on the error, or deviation, from the target pitch. A better understanding may be obtained by referring to the drawings.

[0016] Fig. 1 is a side view showing an aircraft 100 during flight. The aircraft 100 has a pitch or attitude θ indicating an orientation 106 of the aircraft along its longitudinal axis relative to a horizon 108, as known to those skilled in the art. The aircraft 100 includes a flight system 102 that performs various flight-related tasks.

[0017] Referring to Fig. 2, a block diagram illustrates the flight system 102. The flight system 102 includes a controller 120, a display unit 122, and a user interface 124. An interconnect 128 connects the controller 120, the display unit 122, and the user interface 124 for electronic communication. In the present example, the interconnect 128 is a communications or network bus, as known to those skilled in the art. It should be understood that any suitable network topology or physical medium may be used for electronic communication with the flight system 102.

[0018] The control device 120 is a hardware device that includes instructions or control commands of a computer program. In the example presented, the control device 120 is configured to execute the computer program to perform the functions of a conventional flight guidance system (FGS) in addition to performing the functions associated with Fig. 2. The control device may be equipped with one or more processor units (“CPUs”), a microprocessor, an application-specific integrated circuit (“ASIC”), a microcontroller, and / or another suitable device. The control device 120 includes one or more memory units 129 that store electronic data and computer programs. For example, the memory units 129 may be flash memory, spin-transfer torque random access memory (STT-RAM), magnetic memory, phase-change memory (PCM), dynamic random access memory (DRAM), or other suitable electronic storage media. In the example presented, the memory units 129 store logical operations with control commands or instructions that interact with a processor 131 of the control device 120 to execute the steps of the subsequent method.For example, processor 131 may execute the instructions or control commands stored in memory units 129. Furthermore, control device 120 may utilize multiple hardware devices, as would also be apparent to those skilled in the art. Control device 120 has a takeoff operating mode and a fly operating mode, in which a pilot guidance is generated for display on display unit 122 based on various factors, as described below. Control device 120 is configured to control display unit 122 to display the image in the takeoff operating mode and the fly operating mode.

[0019] In the presented example, the user interface 124 is an aircraft control handle configured to receive control movements for adjusting an attitude of the aircraft 100. For example, the user interface 124 may be a side lever control or a lever for receiving instructions from a pilot during manual flight of the aircraft 100. In the presented example, the pilot's instructions are routed or communicated to a hydraulic actuator that moves an elevator of the aircraft 100 to adjust the attitude change.

[0020] The display unit 122 is an electronic screen electronically connected to the controller 120 for displaying information and data in an image 130 according to electronic signals generated by the controller 120 and transmitted to the display unit 122. For example, the display unit 122 may utilize cathode ray tubes ("CRTs"), light-emitting diodes ("LEDs"), plasma panels, liquid crystal displays ("LCDs"), images projected by a digital light processing ("DLP") projector, and / or any other suitable electronic display technology.

[0021] With continued reference to Fig. 2, are Fig. 3 to 5 are schematic diagrams illustrating changes in image 130 during takeoff of aircraft 100. Image 130 includes a horizon indicator 132, a marker 134, a sea level symbol 136, and a flight direction indicator 138. Horizon indicator 132 represents the horizon, sea level symbol 136 represents a pitch attitude or angle of aircraft 100, and flight direction indicator 138 represents a target for marker 134. Marker 134 represents a flight path or deviation between a target pitch or angle and the pitch angle of the aircraft in various operating states of controller 120, as described below. In the example presented, a target attitude 140, an aircraft attitude 142 corresponding to the inclination angle θ and a position difference 144 are not shown on the image 130, but are shown in Fig. 2-5 to illustrate the operations of the control device 120 as they relate to Fig. 6 described below.

[0022] With continued reference to Fig. 2-5 shows Fig. 6 is a flowchart illustrating a method 200 for providing flight guidance to a pilot during a takeoff procedure. Respective steps of method 200 are executed by controller 120. Controller 120 includes control logic with instructions that interact with processor 131 to cause controller 120 to execute the steps of method 200. It should be understood that the steps of method 200 may alternatively be executed by other controllers or devices.

[0023] The controller 120 receives signals indicating an aircraft attitude, a target attitude, and a flight path of the aircraft in operation 210. The aircraft attitude is the pitch attitude or bank angle θ of the aircraft 100, the flight path of the aircraft represents the trajectory of the aircraft 100, and the target attitude is the recommended turn or pitch for executing the takeoff of the aircraft 100. The target attitude may be fixed for all aircraft loads and conditions or may be calculated based on current conditions and current load. For example, the target attitude may be calculated based on the overall aircraft weight, altitude, temperature, configuration, runway slope, or other factors that result in improved performance, or a combination thereof.

[0024] The controller 120 generates a horizon and a sea level indicating the aircraft attitude in the image during operation 212. In the presented example, the controller is configured to generate the sea level 136 a distance below the target attitude 140, which corresponds to the attitude difference between the target attitude and the aircraft attitude.

[0025] The controller 120 determines in step 214 whether a takeoff operating mode is activated. The takeoff operating mode is active when the controller 120 detects that the next attitude change will be to pitch the aircraft from a nose-to-ground attitude to a nose-to-ground attitude. For example, the controller 120 may determine whether the takeoff operating mode is activated based on input signals from a flight control system or flight director, based on whether the aircraft weight is detected in a landing attitude of the aircraft 100, based on an altitude indicator reading, based on other takeoff instructions, or based on a combination thereof. In the presented example, the controller 120 activates the takeoff operating state upon a takeoff procedure of the controller 120.In some embodiments, the controller may activate the takeoff operating mode in response to a de-pitch or de-rotation in a "touch and go" maneuver, where the aircraft 100 is expected to re-pitch and takeoff, as is known to those skilled in the art. In the presented example, the controller 120 is configured to generate the marker in the image during the takeoff operating mode in response to detecting that a pitch angle change has not yet occurred during takeoff.

[0026] If the controller 120 is in the takeoff operating mode, the method 200 continues with step 215 to generate a flight direction indicator at a fixed position in the image. In the presented example, the fixed position is selected based on a minimum takeoff gradient. The method continues with step 216 to generate a marker in the image based on an attitude difference between the aircraft attitude and the target attitude. In the presented example, the controller is configured to generate the marker in the image in the takeoff operating mode a distance below the flight direction indicator that corresponds to the attitude difference 144. Accordingly, during the aircraft pitch, the pilot will use pilot control means to position the marker 134 directly over the tip of the flight direction indicator 138, causing the aircraft to pitch to the target attitude.

[0027] The controller 120 determines whether to transition between the takeoff operating mode and the flight operating mode. For example, the controller 120 may transition in response to at least one indicator indicating that weight is being removed from the wheels, an airspeed indicator, an altitude indicator, or combinations thereof. In the presented example, the controller 120 begins the transition to the flight operating mode at a specified time after weight is removed from the wheels.

[0028] If the controller 120 is in transition, the controller 120 transitions between the takeoff mode and the fly mode by transitioning the marker from the attitude difference to the trajectory-based guidance in step 230. The controller 120 transitions the flight direction indicator from the fixed position to the target trajectory-based guidance in step 232. In some embodiments, the transition is achieved by changing the input signals fed to a complementary filter, as is known to those skilled in the art. In some embodiments, the transition moves the marker at a rate of 0.1 G per second. If the controller 120 is not in transition, the method 200 continues with step 234.

[0029] If the controller 120 is not in the launch mode, then the controller 120 is in the fly mode, and the method 200 proceeds to step 222 to generate the marker in the image based on a target flight path. The controller 120 generates the flight direction indicator in the image based on a target flight path in step 224. For example, the in-flight target flight path angle represented by the marker in the fly mode may be determined to achieve a target airspeed or to continue at a specified bank attitude. The controller 120 proceeds from step 224 to step 234.

[0030] The controller 120 generates a display signal that causes a display unit to display the image in step 234. For example, the controller 120 may generate a video signal or information for a separate video processor to cause the display unit to display the image 130.

[0031] With continued reference to Fig. 2 to 5, an example of an image 130 during a start is described. Image 130 in Fig. 2 illustrates a state in which the aircraft 100 has not yet changed its attitude during takeoff. For example, the aircraft 100 has not yet banked when a pilot of an aircraft initially applies throttle at the beginning of a runway. As described above, the control device 120 is in the takeoff operating state in which a distance between the marker 134 and the flight direction indicator 138 indicates an attitude difference 144.

[0032] As the aircraft 100 builds speed and moves along the runway, the pilot pulls back the control handle to bank the aircraft 100. As the aircraft 100 banks, the bank angle increases. Accordingly, the sea level symbol 136 and the marker 134 in the image 130 move corresponding to the attitude difference 144, as indicated by the movement arrows 180 in Fig. 3 indicated.

[0033] The pilot tilts the aircraft 100 until the mark 134 is positioned directly on the flight direction indicator 138, as shown in Fig. 4. When the mark 134 is positioned directly on the flight direction indicator 138, the attitude difference is zero and the pilot has reached the pitch angle target.

[0034] As the aircraft 100 ascends, the flight direction indicator 138 changes from the fixed position to a position 182 corresponding to a flight path-based guidance device, as indicated by the movement arrow 184 of Fig. 5. In the same way, the marker 134 changes from an attitude difference-based position to a trajectory-based position.

[0035] While at least one exemplary embodiment has been described in the foregoing detailed description, it should be understood that a vast number of variations exist. It should also be understood that the exemplary embodiment or exemplary embodiments are merely examples and are not intended to limit the scope, field of application, or configuration in any way. Preferably, the foregoing detailed description will provide sufficient guidance to those skilled in the art to implement the exemplary embodiment or exemplary embodiments. It should be understood that various changes in the function and arrangement of elements may be made without departing from the scope of the disclosure as set forth in the specification, the following claims, and the legal equivalents thereof.

Claims

[1] A flight system comprising: a display unit configured to display an image; a control device communicatively connected to the display unit and configured to control the display unit to display the image in a control device operating mode for launching and a control device operating mode for flying, the control device further configured to: Receiving signals indicating an aircraft attitude, a target attitude and a flight path of an aircraft; Creating a marker in the image in the launch mode based on an attitude difference between the aircraft attitude and the target attitude; Creating the marker in the image in the flight mode based on the flight path; and Generating a signal that causes the display unit to display the image. [2] The flight system of claim 1, wherein the controller is further configured to generate a flight direction indicator in a fixed position in the image in the takeoff mode of operation and to generate the flight direction indicator based on a flight path in the fly mode of operation. [3] The flight system of claim 1, wherein the controller is configured to switch between a takeoff operating mode and a flight operating mode in response to at least one of: an indicator of a reduction in weight on respective wheels, an indicator of flight speed, and an indicator of altitude. [4] The flight system of claim 1, wherein the controller is configured to generate the marker in the image in the launch mode of operation in response to a launch attitude change not having occurred yet. [5] The flight system of claim 1, wherein the control device is further configured to generate a sea level in the image indicative of an aircraft attitude. [6] The flight system of claim 5, wherein the control device is configured to generate the sea level based on the signals indicating the aircraft attitude and a distance below the target attitude corresponding to an attitude difference. [7] The flight system of claim 1, wherein the controller is configured to generate a flight direction indicator based on a minimum takeoff gradient at a fixed position in the image. [8] The flight system of claim 7, wherein the control device is configured to generate the marker in the image in the takeoff mode of operation below the flight direction indicator at a distance corresponding to the attitude difference. [9] A control device for a flight system, the control device comprising: a processor; and a memory unit operatively connected to the processor, the memory unit having instructions, the instructions and the processor cooperating to configure the controller to control a display unit to display an image in a launch mode of the controller and in a flight mode of the controller, and to: Receiving signals indicating an aircraft attitude, a target attitude and a flight path of an aircraft; in the launch mode of operation, generate a marker in the image based on a position difference between the aircraft attitude and the target attitude; in the flight mode, to generate a marker in the image based on the flight path; and to generate a signal that causes the display unit to display the image. [10] The controller of claim 9, wherein the instructions and the processor further configure the controller to generate a flight direction indicator at a fixed position in the image in the launch mode of operation and to generate the flight direction indicator based on a flight path in the image in the fly mode of operation. [11] The controller of claim 9, wherein the instructions and the processor further configure the controller to transition between the takeoff operating mode and the flight operating mode in response to at least one of indicating a weight reduction on respective wheels, indicating an airspeed, and indicating an altitude. [12] The control device of claim 9, wherein the instructions and the processor further configure the control device to generate the marker in the image in the start-up mode of operation in response to determining that a tilt angle change has not yet occurred. [13] The control device of claim 9, wherein the instructions and the processor further configure the control device to generate a sea level indicative of an aircraft attitude in the image. [14] The control device of claim 13, wherein the instructions and the processor further configure the control device to generate the sea level a distance below the target attitude corresponding to an attitude difference. [15] The controller of claim 9, wherein the instructions and the processor further configure the controller to generate a flight direction indicator based on a minimum takeoff gradient at a fixed position in the image. [16] The controller of claim 15, wherein the instructions and the processor further configure the controller to, in the launch mode of operation, generate the marker at a distance below the flight direction indicator corresponding to the attitude difference. [17] An aircraft comprising: an aircraft control lever configured to receive control movements for adjusting the aircraft; a display unit configured to display an image; and a control device communicatively connected to the display unit and the aircraft control lever, the control device being configured to control the display unit to display the image in an operating mode of the control device for takeoff and in an operating mode of the control device for flight, the control device being configured to: to receive signals indicating an aircraft attitude, an aircraft altitude and a flight path of an aircraft; in the launch mode of operation, generate a marker in the image based on a position difference between the aircraft attitude and a target attitude; in the flight mode, to generate the marker in the image based on the flight path of the aircraft; and to generate a signal that causes the display unit to display the image. [18] The aircraft of claim 17, wherein the controller is configured to generate a flight direction indicator in a fixed position in the takeoff mode of operation and to generate the flight direction indicator based on a target flight path in the flight mode of operation. [19] The aircraft of claim 17, wherein the controller is configured to generate a flight direction indicator based on a minimum takeoff gradient at a fixed position. [20] The aircraft of claim 19, wherein the controller is configured to, in the takeoff mode of operation, generate the marker in the image a distance below the flight direction indicator corresponding to an attitude difference.

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