48 results about "Primary flight display" patented technology

The present invention is directed to a system and methods, embodiments of which provide increased situation awareness information in an improved Synthetic Vision System (SVS). According to the present invention, a Primary Flight Display (PFD), a top-down view Multi-Function Display (MFD), and side-view Vertical Profile Display (VPD) are presented on one user interface with an input device, such as a transparent touch screen for quick and easy data entry. The present invention also provides color shading, such as red, to communicate areas where the aircraft may be in conflict with terrain or obstacles at a point in time in the future.

A flight control system includes a primary flight display having a hover display which facilitates operations in DVE conditions. The hover display includes a radar altitude display, heading drift symbology and lateral drift symbology which assists pilots in the detection of drift, which is common in DVE situations and to provide the pilot with a salient cue pertinent to the approach to hover and landing.

The present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using an various electronic databases, generate intuitive symbols that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors.

A flight control system includes a primary flight display having a hover display which facilitates operations in DVE conditions. The hover display includes a radar altitude display, heading drift symbology and lateral drift symbology which assists pilots in the detection of drift, which is common in DVE situations and to provide the pilot with a salient cue pertinent to the approach to hover and landing.

A display system and method are provided for a vehicle that includes a processor and a display. The processor is adapted to receive terrain data and navigation data operable, in response thereto, to supply one or more image rendering display commands. The display device is coupled to receive the image rendering display commands and operable, in response thereto, to simultaneously render (i) a perspective view image representative of the terrain data and the navigation data and (ii) one or more terrain-tracing lines.

A flight deck display element for an aircraft includes a primary flight display rendered thereon. The primary flight display includes a primary display region having a perimeter, a perspective view of terrain corresponding to a flight deck viewpoint, and an attitude frame surrounding the perimeter of the primary display region. The perspective view of terrain is rendered in the primary display region, and the attitude frame includes a first region and a second region rendered with different visually distinguishable characteristics. The boundaries of the first region and the second region are defined by a current attitude condition of the aircraft.

A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

The invention discloses a system and method for improving viewability of a primary flight display. An aircraft management system is used in displaying a primary flight display screen (100). The primary flight display screen has a predetermined height (H) and includes a horizontal situation indicator (HSI) (102). The aircraft management system includes a processor and a memory device operatively coupled to the processor. The memory device includes programmed computer instructions that instruct the processor to display the HSI for an aircraft. The HSI includes a receding perspective to simulate a three-dimensional (3D) object.

Embodiments of a flight deck display system deployed onboard a rotary wing aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a controller operably coupled to a cockpit display device. The controller is configured to: (i) generate a Primary Flight Display (PFD) on the cockpit display device including a vertical speed indicator; (ii) establish a first vertical speed alert threshold; (iii) compare the first vertical speed alert threshold to a current vertical speed of the rotary wing aircraft; and (iv) if the current vertical speed of the rotary wing aircraft exceeds the first vertical speed alert threshold, produce a first vertical speed alert on the PFD by altering the appearance of the vertical speed indicator in a first predetermined manner.

A display system for a vehicle includes a navigation database storing navigation data; a terrain sensor configured to gather terrain data; a processor adapted to receive the navigation data and the terrain data and operable to supply one or more image rendering display commands based upon the navigation data and the terrain data; and a display device. The display device is coupled to receive the image rendering display commands and operable, in response thereto, to render (i) a perspective view image representative of the terrain data and the navigation data and including terrain and (ii) at least one line on the perspective view image that extends at least partially across the terrain and represents at least one of a ground-referenced range to a fixed location on the terrain and a vehicle-referenced range from the vehicle to a fixed range away from the vehicle.

A primary flight display system is provided for deployment on an aircraft including a barometric altimeter and a secondary altitude-determining device. The barometric altimeter provides a first estimated altitude corresponding to a reference pressure setting, and the secondary altitude-determining device provides a second estimated altitude. The primary flight display system includes a primary flight display (PFD), and a controller coupled to the PFD. The controller is configured to generate: (i) an altitude graphic on the PFD indicative of the first estimated altitude, and (ii) a visual alert on the PFD when the difference between the first estimated altitude and the second estimated altitude exceeds a predetermined error threshold.

The invention discloses an integrated avionics system for light aircrafts, and belongs to the field of integrated avionics systems of aircrafts. The integrated avionics system comprises a navigation subsystem, a communication subsystem and an indicating / recording subsystem; the communication subsystem comprises an audio control panel, a very high frequency station and an earphone microphone component; the indicating / recording subsystem comprises a primary flight display, a multifunctional display, an integrated processor, an engine parameter collector and an aircraft body state collector; the navigation subsystem comprises a flight environment monitoring system, a posture and direction control system and a radio navigation control system; the integrated avionics system disclosed by the invention can replace the original discrete instrument, reduce the incidence of human errors, improve the utilization rate of indicating contents of the indicating system, reduce the use and maintenance costs of general aircrafts, improve the attendance and the security of the general aircrafts and satisfy the client demands.

A display system for a vehicle includes a navigation database storing navigation data; a terrain sensor configured to gather terrain data; a processor adapted to receive the navigation data and the terrain data and operable to supply one or more image rendering display commands based upon the navigation data and the terrain data; and a display device. The display device is coupled to receive the image rendering display commands and operable, in response thereto, to render (i) a perspective view image representative of the terrain data and the navigation data and including terrain and (ii) at least one line on the perspective view image that extends at least partially across the terrain and represents at least one of a ground-referenced range to a fixed location on the terrain and a vehicle-referenced range from the vehicle to a fixed range away from the vehicle.

A method for providing air traffic control (ATC) message data onboard an aircraft is provided. The method establishes communication connections to one or more aircraft onboard communication devices, wherein each of the one or more aircraft onboard communication devices is configured to provide the ATC message data using a particular format; obtains the ATC message data via the communication connections; aggregates the ATC message data, to create an aggregate set of ATC message data; presents a menu of user-selectable options based on an aircraft state, by a display device, wherein each of the user-selectable options is associated with a category of the aggregate set of ATC message data; receives a user input selection of one of the user-selectable options; and presents graphical elements and text associated with the category of the aggregate set of ATC message data, in response to the user input selection.

The present invention is directed to a method of positioning perspective terrain on a SVS (Synthetic Vision System) based on a navigation solution, the vertical component of which is calculated utilizing a terrain database and sensing unit (which provides height above terrain). The terrain database provides elevation of terrain above MSL. A sensor, such as a GNSS sensor, may be utilized to calculate the navigation solution. In alternative embodiments, the navigation solution is calculated differently based upon the phase of flight. In one, the vertical component calculation utilizes the sensing unit at or below the sensing unit's rated altitude. In another, vertical component calculation blends the sensing unit with the sensor. The blending may be based upon percentages based upon altitude or utilize filtering such as Kalman filtering. The present invention is particularly advantageous for close to ground operations, insuring perspective terrain will stay consistent with the real world.

Cockpit display systems and methods are provided for performing Glide Slope (G / S) validation processes during Instrument Landing System (ILS) approaches. In one embodiment, the cockpit display system utilizes validated G / S signals to selectively correct the viewpoint of a Synthetic Vision System (SVS) scene generated on a Synthetic Vision Primary Flight Display (SV-FPD). In such an embodiment, the cockpit display system may include an ILS receiver, a cockpit display device on which the SV-PFD is generated, and a controller operably coupled to the cockpit display device and to the ILS receiver. During an ILS approach, the controller selectively performs a G / S validation algorithm to determine the validity of the G / S signals received during the ILS approach. If determining that the G / S signals are valid, the controller then repeatedly updates the SVS viewpoint during the ILS approach based, at least in part, on the validated G / S signals.

Embodiments of a flight deck display system deployed onboard an aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display device and a controller. The controller is configured to: (i) establish the speed trend of the aircraft over a predetermined time period; (ii) generate a primary flight display on the cockpit display device including a speed trend vector graphic representative of the established speed trend; and (iii) alter the appearance of the speed trend vector graphic in a first predetermined manner if a low speed change condition is detected during at least one of aircraft takeoff and landing.

A system and method displays a synthetic vision system (SVS) image combined with a primary flight display (PFD) including a compass indicating the aircraft heading. An arc on or near the outer edge of the compass indicates the viewing frustum of the SVS view.

A standby flight display system for use on an aircraft is disclosed herein. The aircraft has a primary flight display system that is configured to display a first image on a primary flight display screen. The standby flight display system includes a subsystem configured to determine a dynamic state of the aircraft. The standby flight display system further includes an image generator. The standby flight display system still further includes a processing unit. The subsystem, the image generator, and the processing unit are each independent of the primary flight display system. The processing unit is communicatively coupled with the subsystem and with the image generator and is configured to receive information from the subsystem relating to the dynamic state of the aircraft and to control the image generator to generate a second image overlaying the first image on the primary flight display screen.

The invention aims to provide a control method of data streams of an avionics system of a civil light airplane to solve the problems in the aspects of control real-time, fault-tolerant control and the like of internal data streams of an integrated avionics system in the prior art. The control method comprises the following steps of: firstly, classifying the data streams inside the avionics system of the light airplane into four types, and defining functions and data types of each data field inside the data streams; secondly, according to different attributes of transmission events, dividing each data frame into a periodic type and a conditional type; thirdly, determining different communication cycles, rates and error correction modes; and finally, establishing a standard framework of network transmissions among a main flight display, a multifunctional display, a first integrated processor, a second integrated processor and a plurality of sensors. The control method not only meets requirements on system real-time and reliability, but also has high expandability, supports data channel compounding and data fusion of a plurality of sensors, is low in cost and high in universality, and is widely applied to various integrated display control unit configurations.

A system and method displays a synthetic vision system (SVS) image combined with a primary flight display (PFD) including a compass indicating the aircraft heading. An arc on or near the outer edge of the compass indicates the viewing frustum of the SVS view.

The invention provides a primary flight display instrument in which a symbol—such as a small star or triangle—indicates the bearing to the current waypoint in the flight navigation plan. The display may also show a bearing indication symbol showing a follow-on waypoint in the flight plan. These symbols are preferably located on the horizon line of the primary flight display (or the attitude indicator) providing bearing to the current waypoint in the flight plan and / or to the following waypoint. An image processing unit generates the display, including earth ground and horizon, in a view substantially conformal with a VMC view from the aircraft.

The invention discloses a multi-member airplane avionic system which comprises a mode control panel MCP, a primary flight display PFD, a multifunctional display MFD, an automatic pilot / flight directorAP / FD, a flight management system FMS, a tune control panel TCP, an audio control panel ACP, data interface units DIU, an air data system ADS, an inertial navigation / global positioning system INS / GPS, a very high frequency broadcasting station VHF, an ILS / VOR and a multitask audio management unit AMU. The first data interface unit and the second data interface unit are used for performing dual-redundancy transmission and treatment on airborne equipment data; furthermore, high-reliability flight management can be achieved through the unified flight management system, the problems that a traditional multi-member airplane flight management system has larger volume and weight and higher cost are overcome, and the multi-member airplane avionic system can be applied to upgrading and transforming comprehensive avionic systems of varieties of traditional multi-member airplanes.

A vehicle attitude display such as a Primary Flight Display presents pitch and bank information by displaying a vehicle avatar as fixed, with respect to a moving artificial horizon whilst displaying a movable symbol at a position along the vehicle avatar that is proportional to the symmetry of the vehicle. Parts of the display are dynamically emphasised or de-emphasised to support rapid assimilation of key data. Display format may be dynamically adjusted depending on vehicle use conditions. Display is intended for use both in-vehicle, and remotely.

Improved systems and methods for dynamic readouts on a primary flight display are provided. The system includes a computer system configured to receive and process aircraft status data and flight plan data to command a display system to overlay on the image, (i) an analog indicator of the airspeed, (ii) an analog indicator of altitude, (iii) a digital airspeed indicator, and (iv) a digital altitude indicator. The system continuously determines whether steady flight conditions are occurring. Steady flight conditions include one or both of: constant airspeed and constant rate of change of airspeed. When the steady flight conditions are occurring, (i) and (ii) are removed from the image. When the steady flight conditions are no longer occurring, (i) and (ii) again overlaid on the image.