Abstract: A super resolution processor/receiver to discriminate superimposed secondary surveillance radar (Mode S, Mode A/C) replies and squitter that uses frequency-domain analysis to suppress interference between replies. In particular, the processor/receiver uses a spectral super-resolution method to estimate carriers of reply signals (every reply has a carrier that could be slightly different from the others). These frequency analyses, applied with particular timing referring to the signal that effectively carried the information, allow to estimate the information on SSR Mode S/Mode A/C replies.

Abstract: A super resolution processor/receiver to discriminate superimposed secondary surveillance radar (Mode S, Mode A/C) replies and squitter that uses frequency-domain analysis to suppress interference between replies. In particular, the processor/receiver uses a spectral super-resolution method to estimate carriers of reply signals (every reply has a carrier that could be slightly different from the others). These frequency analyses, applied with particular timing referring to the signal that effectively carried the information, allow to estimate the information on SSR Mode S/Mode A/C replies.

Abstract: A ground-based CFIT warning system provides pilots with CFIT alerts. The system is based upon a ground-based tracking system, which provides surveillance of aircraft, such as the AirScene™ multilateration system manufactured by Rannoch Corporation of Alexandria, Va. The system monitors both horizontal and vertical positions of aircraft. When an aircraft has been determined to be operating below safe altitudes, or too close to obstructions, the pilot is provided with a warning. The warning may be delivered via the pilot's voice communications and/or a data link or the like.

Abstract: An algorithm for improved tracking of Air Traffic Control Radar Beacon System transponders is disclosed. The algorithm can be combined with a system that includes an interrogator which transmits an interrogation signal to an associated vehicle transponder at a first frequency, preferably 1030 MHZ in accordance with FAA regulations, and a receiver array which receives the transponder reply signal transmitted by the transponder at a second frequency, preferably 1090 MHZ in accordance with FAA regulations. An angle of arrival processor calculates an angle of the received reply signal, and a position processor calculates the vehicle position based on at least the received angle data.

Abstract: The invention relates to a radar system for active obstacle warning and imaging of the surface of the earth, working in the pulse frequency or FM-CW range, which can be used in on-line operation in real time, comprising a plurality of antenna elements for sending and receiving radar signals, which are arranged on the fuselage of an aircraft, and which may be turned on and scanned sequentially, whereby a synthetic aperture can be generated by means of periodic sending and receiving of the antenna elements. According to the invention, the antenna elements are arranged along the curved surface of the aircraft contour, whereby a SAR processor is present, which analyzes the data obtained from the antenna elements and displays them as processed radar images on board the aircraft, in a virtual cockpit.

Abstract: A collision avoidance sense and avoid capability for an aircraft or other vehicle that monitors a sphere or other safety zone/cocoon about the vehicle. A light-detecting camera or other sensor receives a signal return if any object enters the safety cocoon. Once an object is detected in the cocoon, a signal is sent to the onboard sense and avoid computer and corrective action is taken. The system is capable of autonomous operation, and is self-contained and does not require additional hardware installations on target vehicles. The size and shape of the safety cocoon monitored by the sensors adjusts according to the speed and motion vectors of the aircraft or other vehicle, so as to maximize efficient use of sensor capabilities and minimize the size, cost and power requirements of the system.

Abstract: An improved system and methods for correlating an interrogation-based air traffic surveillance intruder, such as an Traffic alert and Collision Avoidance System (TCAS) intruder, and a GPS-based air traffic surveillance target, such as an Automatic Dependent Surveillance Broadcast (ADS-B) target to minimize or eliminate the display of two symbols for the same intruder/target on the CDTI of an aircraft. The method comprises the steps of receiving ADS-B data at a processing unit and calculating select component deltas for the ADS-B data versus an entry in a TCAS intruder file. Progressive weights are assigned to the deltas and the progressive weights are summed, resulting in a total confidence score. Total confidence scores of ADS-B target and TCAS intruder pairs are compared to determine correlation between the ADS-B target and the TCAS intruders.

Abstract: A method and system for collision avoidance, carried by each aircraft, includes a miniature MEMS (MicroElectroMechanical Systems) IMU (Inertial Measurement Unit), a miniature GPS (Global Positioning System) receiver, a display, a data link receiver/transmitter, and a central processing system. Each aircraft carries a GPS receiver coupled with a self-contained miniature IMU for uninterrupted position determination. This position information is shared with other aircraft over an RF (Radio Frequency) data link. An intelligent display shows the relative positions of the aircraft in the immediate vicinity of the host aircraft and issues voice and flashing warnings if a collision hazard exists. This system provides situational awareness to the pilot and enhances the safety of flight.

Abstract: An adaptive cruise control system is provided for tracking a target vehicle through a curve. The adaptive cruise control system tests whether the target vehicle is traveling along the curve or whether the target vehicle is changing lanes. The test includes monitoring a change in travel directions between the target vehicle and the adaptive cruise control vehicle. In one embodiment, the test monitors a change relative velocity versus azimuth angle.

Abstract: The invention relates to the input of speed limiting values into a speed limiter in a vehicle. The speed limiting value which is to be complied with is set by activating a key (7) on an input device (8) one or more times. That speed limiting value of the predefined speed limiting values which is the next highest in relation to the current speed of the vehicle is selected. If the current speed of the vehicle is higher than the highest predefined speed limiting value, the speed limiter is deactivated or the speed of the vehicle plus a speed difference is accepted as the speed limiting value. In exceptional situations, the speed limiter can be temporarily suspended, it being possible for an exceptional situation to be, in particular, the upward transgression of the predefined speed limiting value or a rapid depression of the gas pedal.

Abstract: A method of terrain mapping and/or obstacle detection for aircraft, comprising:

Abstract: A display system is disclosed for displaying air traffic symbology from a plurality of different types of air traffic surveillance systems on a single monitor. A display device includes a processor for generating display symbology from TCAS, SKE and ADS-B information, and a monitor for displaying the generated symbology in a uniform format.

Abstract: The present invention provides airline mechanics with an electronic maintenance terminal (MT) that displays real time central maintenance computer (CMC) data screens. The invention provides the mechanic with the ability to access fault isolation manual (FIM) troubleshooting procedures via an internal software hot link between the CMC fault code and the FIM procedure. The FIM data is a subset of the electronic portable maintenance aid (PMA) data. In addition to faults the present invention also links flight deck effect (FDE) EICAS messages to FIM troubleshooting procedures.

Abstract: The invention relates to a speed limiter in a vehicle. The speed limiting value which is to be complied with is set by activating a key (7) on an input device (8) one or more times. That speed limiting value of the predefined speed limiting values which is the next highest in relation to the current speed of the vehicle is selected. If the current speed of the vehicle is higher than the highest predefined speed limiting value, the speed of the vehicle plus a speed difference is accepted as the speed limiting value. In exceptional situations, the speed limiter can be temporarily suspended, it being possible for an exceptional situation to be, in particular, the upward transgression of the predefined speed limiting value or a (rapid) depression of the gas pedal.

Abstract: A system having replaceable subsystems is operable in a certified configuration after installation of a replacement subsystem. The system includes several subsystems each installed at an interface. For each subsystem, the interface includes memory having a description of the operating environment for that subsystem. The memory stores modules each having a signature, for example, a cyclic redundancy code (CRC). After installation of a replacement subsystem, a processor in the subsystem checks a list of signatures. Each signature corresponds to a module that is certified for use by an application program of the subsystem. If a listed signature corresponds to a module that is available in the memory, is desirable to be used, and the subsystem is not presently configured to use such a module, the subsystem reads the module, integrates the data of the module into an operating configuration, and operates thereafter in accordance with the updated operating configuration.

Abstract: A traffic collision avoidance system has a transponder with an interrogation monitoring engine for receiving interrogations and an interrogation response engine for inhibiting responses to the interrogations if the interrogations are air traffic control interrogations and the transponder is in a quiet mode. Typically the transponder enters quiet mode during military formation flight if the aircraft in which the transponder is installed is not a tail or lead member of the formation.

Abstract: A system and a method for distance measurement utilizes a radio system. The distance is measured by determining the time it takes a pulse train to travel from a first radio transceiver to a second radio transceiver and then from the second radio transceiver back to the first radio transceiver. The actual measurement is a two step process. In the first step, the distance is measured in coarse resolution, and in the second step, the distance is measured in fine resolution. A first pulse train is transmitted using a transmit time base from the first radio transceiver. The first pulse train is received at a second radio transceiver. The second radio transceiver synchronizes its time base with the first pulse train before transmitting a second pulse train back to the first radio transceiver, which then synchronizes a receive time base with the second pulse train. The time delay between the transmit time base and the receive time base can then be determined.

Abstract: This invention relates to a robust data fusion procedure of multi-digital surveillance information mounted on an aircraft per se capable of receiving surveillance information of other aircrafts, including traffic information service (TIS), traffic alert and collision avoidance system (TCAS) and automatic dependant surveillance broadcasting (ADSB). The data fusing procedure of the multi-digital surveillance information of this invention is capable of applying data fusion module to provide an effective surveillance data fusion procedure for fusing the data produced by surveillance source (ADSB, TCAS and TIS). The traffic information of the aircraft per se is provided by GNSS while outputting the status information of other aircrafts in the surrounding airspace to the cockpit display traffic information (CDTI) system to enhance airborne security.

Abstract: Methods, apparatus and program product are provided to obtain a shortened holding pattern exit path for an aircraft from its current position (CP) in or entering a holding pattern to an allowed exit point (EP) of the holding pattern. The flight management system (FMS) determines which segment of the holding pattern the aircraft is currently on, i.e., A, B, or C defined in terms of the holding pattern turn points (TP1, TP2, TP3, TP4) and the waypoint (SP) which is symmetrical to the desired EP. The FMS compares the aircraft CP with EP and SP locations and directs turns at the appropriate waypoints to give the shortest allowed exit pathway. Both Type I and Type II holding pattern entries are accommodated.

Abstract: In one embodiment, a method for controlling an aircraft comprises providing an attitude error as a first input into a neural controller and an attitude rate as a second input into the neural controller. The attitude error is calculated from a commanded attitude and a current measured attitude, and the attitude rate is derived from the current measured attitude. The method also comprises processing the first input and the second input to generate a commanded servo actuator rate as an output of the neural controller. The method further comprises generating a commanded actuator position from the commanded servo actuator rate and a current servo position, and inputting the commanded actuator position to a servo motor configured to drive an attitude actuator to the commanded actuator position. The neural controller is developed from a neural network, wherein the neural network is designed without using conventional control laws, and the neural network is trained to eliminate the attitude error.

Abstract: A surveillance and collision avoidance system provides a presentation of situational awareness information for display that includes a compound symbol for each target spaced at a distance and bearing relative to a host symbol. The target compound symbol includes indicia of (a) whether the target is airborne or on the ground; (b) whether the target is a civil aircraft, a military aircraft identified as a formation member with the host aircraft, or a military aircraft not identified as a formation member with the host aircraft; (c) whether a ground track for the target is unknown, known by passive surveillance, or known by active surveillance; (d) for civil aircraft, whether the target is the subject of no advisory, a traffic advisory, or a resolution advisory; and (e) for a military aircraft, whether the target is the subject of no encroachment advisory, an unintended encroachment advisory, or an intended encroachment advisory. Subsystems selectively use an active or a passive mode of surveillance.

Abstract: A remote control signal, such as a signal from a GPS satellite, is received at a servant aircraft. If the remote control signal is valid, a processor on the servant aircraft prevents or inhibits anyone on the servant aircraft from controlling the flight or course of the servant aircraft. The remote control signal controls the flight and/or course of the servant aircraft. The remote control signal may come from an escort aircraft.

Abstract: A method and apparatus to automatically prevent aircraft collisions. An aircraft control system receives internal aircraft data from aircraft sensors and external aircraft data received by radios or transponders. The internal and external aircraft data is provided as input data to at least three microprocessor based central processing units that process the input data and generate recommended control signals. The recommended control signals are received by a control that determines a resultant control signal that is sent to the cockpit and/or a transmitter. If the control is disabled, a backup control determines a resultant control signal that is sent to the cockpit and/or a transmitter. The cockpit outputs the control signal and passes the control signal through a filter. The filter determines if no action is to be taken or if adjustments are to be made to aircraft flight control surfaces and/or the engine.

Abstract: A signal is received from an off limits facility and it is determined from the signal whether an aircraft is within a distance of the off limits facility. The course and/or flight of the aircraft is changed if the aircraft is within the distance of the off limits facility. A signal is received from an airport and it is determined from the signal whether an aircraft will be allowed to take off from the airport. The aircraft is prevented from taking off if the signal from the airport indicates that the aircraft should be prevented from taking off. A signal is received from a satellite and it is determined from the signal whether an aircraft is within a distance of an off limits facility. The course and/or flight of the aircraft if the aircraft is changed if the aircraft is within the distance of the off limits facility.

Abstract: An integrated surface moving map advisory system that provide selectable amounts of simplified airport layout information, simultaneously with authorized ground movement authority in order to provide highly informative and intuitive guidance with respect to all aspects of operating an aircraft or other vehicle in a controlled geographical area. The advisory system may be further enhanced by the additional overlay of symbols representing other airport traffic along with the general intentions of such traffic.

Abstract: A method of improving a sealing between a purge mechanism and a printhead includes the steps of providing a purge cap with a perimetrical sealing lip; and exercising the perimetrical sealing lip of the purge cap against the sealing surface of the printhead. The exercising is effected by generating a repetitive relative movement between the sealing surface of the printhead and the perimetrical sealing lip of the purge cap.

Abstract: Systems, methods and protocol for assuring separation of aircraft during parallel approaches. The systems, methods and protocol function in cooperation with existing TCAS to facilitate approaches of multiple aircraft on closely-spaced parallel runways. The systems, methods and protocol utilize data transmissions from equipped aircraft to obtain tracking information which is used in separation algorithms to generate alerts to an observer of possible threats. The systems, methods and protocol facilitate parallel approaches to closely-spaced parallel runways under Instrument Approach Procedure.

Abstract: A collision prediction and maneuver method determines which ones of many potential target objects have a close conjunction within a gross miss distance with a subject object by trajectory propagation, then determines which one of the conjunctive objects have a high collision probability within a critical miss distance, and then determines an optimum vehicle maneuver to reduce the probability of colliding with another colliding object by determining the maneuver direction, magnitude, and time so that the least amount of propellant is consumed while avoiding potential collisions within miss distance margins. The method includes computational efficiencies in collision probability calculations using trajectory propagations and contour integrations and efficiencies in optimum avoidance maneuvering using gradient and searching computations.

Abstract: A collision prediction and maneuver method determines which ones of many potential target objects have a close conjunction within a gross miss distance with a subject object by trajectory propagation, then determines which one of the conjunctive objects have a high collision probability within a critical miss distance, and then determines an optimum vehicle maneuver to reduce the probability of colliding with another colliding object by determining the maneuver direction, magnitude, and time so that the least amount of propellant is consumed while avoiding potential collisions within miss distance margins. The method includes computational efficiencies in collision probability calculations using trajectory propagations and contour integrations and efficiencies in optimum avoidance maneuvering using gradient and searching computations.

Abstract: A collision prediction and maneuver method determines which ones of many potential target objects have a close conjunction within a gross miss distance with a subject object by trajectory propagation, then determines which one of the conjunctive objects have a high collision probability within a critical miss distance, and then determines an optimum vehicle maneuver to reduce the probability of colliding with another colliding object by determining the maneuver direction, magnitude, and time so that the least amount of propellant is consumed while avoiding potential collisions within miss distance margins. The method includes computational efficiencies in collision probability calculations using trajectory propagations and contour integrations and efficiencies in optimum avoidance maneuvering using gradient and searching computations.

Abstract: A method and device for deriving and displaying advanced TCAS information.

Abstract: A display system is disclosed for displaying air traffic symbology from a plurality of different types of air traffic surveillance systems on a single monitor. A display device includes a processor for generating display symbology from TCAS, SKE and ADS-B information, and a monitor for displaying the generated symbology in a uniform format.

Abstract: A method to determine a target azimuth with a radar. The radar sends out a wave of N-pulse bursts. The method includes in one burst: splitting up a N-pulse burst into two half bursts, of a front burst and a rear burst; filtering the front and rear bursts to associate an azimuth value &thgr;1 and an amplitude value A1 with the front burst, and an azimuth value &thgr;2 and an amplitude value A2 with the rear burst; and obtaining the target azimuth Az at a value corresponding to a maximum of a Gaussian curve passing through points having components (&thgr;1, A1) and (&thgr;2, A2).

Abstract: A tamper-resistant apparatus located on board of an aircraft for avoiding a restricted air space (RAS) comprising: (a) a tamper-resistant restricted air space (TAP-RAS) database configured to include a set of coordinates that determines the RAS; and (b) a navigational processor configured to navigate the aircraft around the RAS, if a valid overriding command is not generated. The navigational processor includes: a Satellite Positioning System (SATPS) configured to substantially continuously obtain a set of real time position coordinates of the aircraft; a restricted airspace controller configured to receive a set of real time data including the set of coordinates that determines the RAS, the set of real time position coordinates; and configured to analyze the set of real time data in order to substantially continuously generate a set of real time commands; and an aircraft controller configured to navigate the aircraft utilizing the real time set of commands around the RAS.

Abstract: A traffic collision avoidance system has a transponder with an interrogation monitoring engine for receiving interrogations and an interrogation response engine for inhibiting responses to the interrogations if the interrogations are air traffic control interrogations and the transponder is in a quiet mode. Typically the transponder enters quiet mode during military formation flight if the aircraft in which the transponder is installed is not a tail or lead member of the formation.

Abstract: An airborne collision avoidance system includes a receiver stage constructed and arranged to detect (a) at a first radio frequency, first interrogation signals, and first collision resolution advisory (RA) signals transmitted from other nearby aircraft, and (b) at a second radio frequency, first acquisition signals including position information with respect to the nearby aircraft, and first reply signals from the nearby aircraft. A transmitter stage is constructed to produce (a) at the first radio frequency, second interrogation signals and second collision RA signals, and (b) at the second radio frequency, second acquisition signals including position information with respect to the given aircraft, and second reply signals from the given aircraft in response to the first interrogation signals. Tracking and collision avoidance information derived by a system processor from the detected first acquisition and first RA signals is shown on a cockpit display.

Abstract: An automated terrain awareness and avoidance system includes a transmitter located in a region to be protected from controlled flight into terrain accidents. The transmitter transmits an identification value to an aircraft. In response, a safety checking routine on the aircraft identifies a danger zone around the transmitter, and determines whether the aircraft has (or will) enter the danger zone. If the safety checking routine determines that the aircraft has (or will) enter the danger zone, the safety checking routine determines a safe route and engages the autopilot, which steers the aircraft along the safe route. The safety checking routine also causes a password to be transmitted to an air route traffic control center (ARTCC). The autopilot is disengaged if the safety checking routine determines the aircraft is no longer on course to enter the danger zone, or when the password, which must be received from the ARTCC, is entered.

Abstract: A formation collision avoidance system includes a Traffic Alert and Collision Avoidance System (TCAS) having a passive mode and an active mode. The passive mode enables several members of an aircraft formation to fly without actively interrogating using TCAS while only one or few formation members are actively interrogating. Formation members in passive mode maintain awareness of current air and ground traffic conditions using networked surveillance information provided over a communications link between formation members in active mode and formation members in passive mode. The networked surveillance information includes positional and intent information of current air/ground traffic obtained from ADS-B broadcasts and replies to the actively interrogating members of the formation. The communications link utilizes Station Keeping Equipment (SKE) already existing on certain aircraft.

Abstract: A midair collision avoidance system (MCAS) employs an existing design of Traffic Alert and Collision Avoidance System (TCAS) as a module and seamlessly integrates it with a customized tactical module which is capable of providing unique tactical avoidance guidance control and display. The tactical module handles all phases of a tactical mission, including formation flight (e.g., formation fall-in, arming formation flight, engaging formation flight following, and formation brake-away), and an air-refueling sequence (e.g., rendezvous, linkup, re-fueling, and disengaging air-refueling). The tactical module divides the air space around the aircraft into advisory, caution, and warning zones and for each provides display, tone and voice alerts to facilitate pop-up avoidance guidance commands. Military aircraft can thus effectively avoid mid air and near mid air collision situations in all three different operation modes: air traffic control (ATC) management mode, tactical mode, and a mixed mode.

Abstract: A method for determining a position of a doppler radar target in aircraft body coordinates is described. The method includes calculating values for doppler circle equations, in doppler coordinates, based upon a range to the target, a vehicle velocity, and a center frequency and bandwidth of a doppler swath filter. Further, an interferometric circle in body coordinates is calculated based upon a range to the target, and an interferometric angle. The doppler circle equations are transformed into body coordinates utilizing received pitch, roll and yaw information. Finally, an intersection of the interferometric circle equations with the transformed doppler circle equations is calculated, the intersection being the position of the target in body coordinates.

Abstract: A system having replaceable subsystems is operable in a certified configuration after installation of a replacement subsystem. The system includes several subsystems each installed at an interface. For each subsystem, the interface includes memory having a description of the operating environment for that subsystem. The memory stores modules each having a signature, for example, a cyclic redundancy code (CRC). After installation of a replacement subsystem, a processor in the subsystem checks a list of signatures. Each signature corresponds to a module that is certified for use by an application program of the subsystem. If a listed signature corresponds to a module that is available in the memory, is desirable to be used, and the subsystem is not presently configured to use such a module, the subsystem reads the module, integrates the data of the module into an operating configuration, and operates thereafter in accordance with the updated operating configuration.

Abstract: A method of processing reply signals received in response to an interrogation by a secondary surveillance radar system. The method includes the steps of receiving a reply signal from each of a plurality of targets, and enabling each of a plurality of target mode blocks having a predefined mode to select from the reply signals. The method further includes the step of correlating the selected reply signal to the target mode block that selected same.

Abstract: A system for detecting, identifying and validating the existence of ordinance located atop or buried beneath the ground including at least one aerial platform capable of powered flight, a base station including apparatus for launching, storing, and refueling the at least one aerial platform, the base station further including apparatus for communicating with the aerial platform, and a control station remote from the base station and including apparatus for communicating with the base station such that a human operator at the control station is capable of communicating flight path instructions to the base station to be communicated to each of the aerial platforms.

Abstract: An apparatus and system for preventing a hijacker from intentionally causing an aircraft to crash into a structure such as a building. Protected structures or areas are equipped with transmitters which transmit a coded signal when an aircraft is detected inside a minum safe range. Upon receiving the coded signals, a protective control unit on-board the aircraft overrides any commands from the pilot cockpit and automatically diverts the aircraft to avoid a collision. When the aircraft is a safe distance from the protected structure, the protective control unit deactivates and the controls are restored to the pilot cockpit. In an alternative embodiment, the protective control unit can be activated and controlled remotely to land a hijacked aircraft.

Abstract: An apparatus, method and computer program product for suppressing an alert generated by a terrain awareness system rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.

Abstract: An aircraft system and method for determining when to attempt acquisition of an intruder for active tracking. A link reliability score associated with the intruder is adjusted based upon the signal strength of transmissions, the frequency of the transmissions, and the number of previous attempts to acquire the intruder for active tracking.

Abstract: A ROSAR wire detection method is based upon ROSAR focusing of entire segments of wire. By generating a wire reference signal comprised of a sum of coherent reference signals, the basis for reliable wire detectability is provided.

Abstract: An aircraft system and method for determining when to attempt acquisition of an intruder for active tracking. A link reliability score associated with the intruder is adjusted based upon the signal strength of transmissions, the frequency of the transmissions, and the number of previous attempts to acquire the intruder for active tracking.

Abstract: A midair collision avoidance system (MCAS) employs an existing design of Traffic Alert and Collision Avoidance System (TCAS) as a module and seamlessly integrates it with a customized tactical module which is capable of providing unique tactical avoidance guidance control and display. The tactical module handles all phases of a tactical mission, including formation flight (e.g., formation fall-in, arming formation flight, engaging formation flight following, and formation break-away), and an air-refueling sequence (e.g., rendezvous, linkup, re-fueling, and disengaging air-refueling). The tactical module divides the air space around the aircraft into advisory, caution, and warning zones and for each provides display, tone and voice alerts to facilitate pop-up avoidance guidance commands. Military aircraft can thus effectively avoid mid air and near mid air collision situations in all three different operation modes: air traffic control (ATC) management mode, tactical mode, and a mixed mode.

Abstract: The invention relates to compliance with the safety distances between aircraft travelling, in a queue, one behind the other, through a prescribed air corridor. It is more especially concerned with a process allowing an aircraft knowing its position and those of the various aircraft flying in its close vicinity, for example by virtue of the ADS-B system, to manage by itself its separation distance with respect to another aircraft taken as reference. Such a process is an aid afforded to the crew of an aircraft and to the control authority regulating the traffic in the relevant air corridor.