53 results about "Aircraft vectoring" patented technology

A method of aircraft navigation via receiving signals emitted by other aircraft and corresponding reply message transmitted by ground transceivers and the using a new diverse-ranging algorithm that solves for the positions of a eavesdropping aircraft and the positions of direct-reply aircraft emitting the signals received by the eavesdropping aircraft.

A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g., one aircraft per minute), which would enable the traffic controllers to optimize runway traffic without having to stack the aircraft in holding patterns and thereby waste fuel. Notably, although an example of an aircraft navigation and control system and method is disclosed, the system and method can be implemented for any type of vehicle (e.g., aircraft, spacecraft, ship, submarine, bus, train, automobile, etc.) whose operator desires to reach a particular location at a specified time.

A method and apparatus for assisting in management of unmanned aerial vehicles. Planned routes are identified for the unmanned aerial vehicles. The planned routes are displayed on a map. A set of planned routes is identified that is within a predefined distance of a selected planned route during substantially a same point in time within a viewing area on the map.

A wireless transmitter device that has a baseline ‘off’ status, turning its data transmission module ‘on’ only under certain specific circumstances, thus allowing the device to be used on aircraft without concern of the device activating and transmitting location data that might interfere with the aircraft navigation and/or communication systems. The data transmission module may be turned on manually (i.e., manual activation), may be activated based on time (i.e., time-based activation), or may be activated based on motion (i.e., motion-based activation). Activation of the data transmission module occurs only after it has been determined that it is safe to activate the module(s), for example, if no motion of the device has been sensed for a predetermined period of time. Only after the device has assuredly determined that the aircraft is in a mode where data transmission is allowed (e.g., not in flight) is the data transmission module activated.

The present invention provides a system and method for aircraft to determine own position and navigate using a navigation heartbeat signal broadcast on a DME uplink and/or a Mode-S uplink frequency. The present invention enables deep integration between the existing navigation systems (DME interrogation-reply ranges and GPS/WAAS raw TDOA or pseudo range measurements) and the DME heartbeat TDOAs or Mode-S heartbeat TDOAs to provide a highly accurate navigation positioning capability and provide necessary backup capability in lieu of GPS to maintain the necessary RNP/RNAV capability and avoid degrading aircraft operational safety.

A method and apparatus for assisting in management of a number of unmanned aerial vehicles. Symbols used to display a number of pre-planned routes for the number of unmanned aerial vehicles are identified on a top-down view of the number of pre-planned routes. Flight information with respect to time for the number of unmanned aerial vehicles on a number of timelines is displayed using the symbols identified as being used to display the number of pre-planned routes for the number of unmanned aerial vehicles on the top-down view of the number of pre-planned routes.

The invention relates to a device for assisting in the navigation of an aircraft in an airport zone comprising a surface navigation system and means of acquiring in real time, while navigating on the ground or in flight, new information or temporary information relating to the navigation in the airport zone. The surface navigation system uses information relating to the navigation in the airport zone. The information is previously stored in a database on board the aircraft. The device includes means for decoding and analysing the new or temporary information relating to the navigation in the airport zone, means of filtering the information according to the airport concerned and the validity date of the information, means of correlating the information with the information previously stored, and means of displaying the information.

Systems, apparatuses and methods for landing an unmanned aircraft on a mobile structure are presented. Sensors on the aircraft identify a predetermined landing area on a mobile structure. The aircraft monitors the sensor data to maintain its position hovering over the landing area. The aircraft estimates a future attitude of the surface of the landing area and determines a landing time that corresponds to a desired attitude of the surface of the landing area. The unmanned aircraft executes a landing maneuver to bring the aircraft into contact with the surface of the landing area at the determined landing time.

A method of determining conflicting flight paths between a first and a second airborne vehicle is provided, wherein each vehicle comprises an aircraft-to-aircraft navigational communication system having a navigational device. First, a position and a velocity vector are determined for each of the airborne vehicles. A cylindrical volume is then defined about the first airborne vehicle. A separation distance is then determined between the vehicles at a selected time and using a great circle earth model. An accuracy factor is thereafter determined for the position of each vehicle. The separation distance is then modified by the accuracy factor. A determination is then made as to whether the modified separation distance is within the cylindrical volume about the first airborne vehicle during a time range to thereby determine whether conflicting flight paths exist between the vehicles. An associated system and computer software program product are also provided.

A navigation technique for a vehicle employs an inertial reference system to derive a first position indication and a first velocity value. A first receiver processes signals of a global positioning system from which a second position indication and a second velocity value are derived. A second receiver processes signals from a plurality of distance measuring equipment stations at fixed positions on the earth and determines the distance between the vehicle and each of those stations. A third position indication is derived from those distances. A Kalman filter function is applied to the first, second and third position indications and to the first and second velocity values to compensate for uncertainty in the first position indication and in the first velocity value and thereby produce a vehicle position estimate and a vehicle velocity estimate.

An exterior aircraft navigation light for an aircraft having a nominal forward flight direction and being able to fly into the nominal forward flight direction as well as into a plurality of further flight directions, such as sideways or backwards, has at least one light emission unit and control circuitry coupled to the at least one light emission unit, wherein the exterior aircraft navigation light is configured such that each of the at least one light emission unit has a unit-specific light emission direction that has a pre-defined horizontal angle with respect to the nominal forward flight direction, and wherein each of the at least one light emission unit includes a multi-color light source configured to emit red light, white light and green light, and an optical system for conditioning the red light, the white light and the green light emitted by the multi-color light source.

An aircraft display system is provided for rendering at least aircraft estimated position uncertainty (EPU) and/or vertical estimated position uncertainty (VEPU) values non-numerically and in a fairly intuitive manner. The system may also render the EPU and VEPU values non-numerically for other traffic entities within range of the aircraft.

The invention relates to a general airplane landing radial line navigation method. The general airplane landing radial line navigation method comprises the following steps of 1, building a landing radial line by airborne navigation equipment according to airplane real-time position information provided by an airplane instrument, navigation information provided by a ground navigation station, and a received landing radial line building instruction, carrying out calculation, and displaying the landing radial line and a reverse-direction extending line of the landing radial line by cockpit display equipment, and 2, carrying out landing according to the landing radial line and the navigation information provided by the ground navigation station, guiding an airplane to the reverse-direction extending line of the landing radial line, and adjusting the airplane to make it fly or land along a direction of the landing radial line. The general airplane landing radial line navigation method solves the problem that the existing landing navigation method has a large potential safety hazard in a zone without ground navigation facilities. The general airplane landing radial line navigation method is a real-time, visual, convenient and reliable airplane navigation calculation method, improves an implementation method of real-time flight guidance of a general airplane and pilot autonomous operation display, and provides a visual and accurate landing navigation method.

The invention relates to an aircraft navigation aid method. It comprises the following steps of defining an area to be sensed to the right and to the left of a first hypothetical path of the aircraft, sensing, for each of the two areas to be sensed to the right and to the left, a corresponding predefined underlying relief, in order to identify dangerous sub-zones to the right and/or to the left, computing, for each of the dangerous sub-zones to the right and/or to the left, a time ΔT remaining to begin an avoidance maneuver before a point of no return, and determining for the dangerous sub-zones to the right a minimum ΔT denoted ΔT right and/or for the dangerous sub-zones to the left a minimum ΔT denoted ΔT left, establishing a navigation aid from ΔT right and/or ΔT left.