Disclosed is a method and apparatus for generating a radar signal, in which performance of radar detection is ensured while increasing a spectrum efficiency in a radar network. The method comprises generating a set of frequency-modulation waveforms, generating an orthogonal code set, generating a set of coded frequency-modulation waveforms through element operation between the set of frequency-modulation waveforms and the orthogonal code set, calculating an objective function for the set of frequency-modulation waveforms with regard to a different set of coded frequency-modulation waveforms and previous sets of coded frequency-modulation waveforms, and selecting a current polyphase code set as an optimized polyphase code set when a result of current calculation is better or smaller than a result of previous iteration, and performing phase perturbation by replacing an element randomly selected in the current polyphase code set selected as the optimized polyphase code set with another admissible-phase element.

A system for detecting airborne objects within a shared field of view includes a first transceiver and a second transceiver. The first transceiver is positioned in a first discrete location and has a first field of view that represents a detection area of the first transceiver and the second transceiver is positioned in a second discrete location and has a second field of view that represents the detection area of the second field of view. The first field of view and the second field of view intersect one another to create the shared field of view. Both the first transceiver and the second transceiver are configured to emit an array of signals towards the shared field of view. Each signal of the array of signals includes a unique signature including information for determining an actual distance between either the first transceiver or the second transceiver and the airborne object.

A system for detecting airborne objects within a shared field of view includes a first transceiver and a second transceiver. The first transceiver is positioned in a first discrete location and has a first field of view that represents a detection area of the first transceiver and the second transceiver is positioned in a second discrete location and has a second field of view that represents the detection area of the second field of view. The first field of view and the second field of view intersect one another to create the shared field of view. Both the first transceiver and the second transceiver are configured to emit an array of signals towards the shared field of view. Each signal of the array of signals includes a unique signature including information for determining an actual distance between either the first transceiver or the second transceiver and the airborne object.

A density of Mode S interrogations and responses in the environment covered by a secondary radar is characterized according to the following steps: a first step wherein the radar: detects and locates Mode S targets by way of their synchronous responses to the interrogations emitted by the radar; detects asynchronous responses emitted by the Mode S targets, and not elicited by the radar; for each target, associates its asynchronous responses with its synchronous response to the radar; a second step wherein the radar: based on the association, determines the response rate of each target by counting the number of synchronous and asynchronous responses received from the target per given time period; with the environment being divided into elementary space cells, determines the response rate per cell by counting the number of synchronous and asynchronous responses received by each target in each cell, the rate characterizing the density of Mode S interrogations per cell.

A density of Mode S interrogations and responses in the environment covered by a secondary radar is characterized according to the following steps: a first step wherein the radar: detects and locates Mode S targets by way of their synchronous responses to the interrogations emitted by the radar; detects asynchronous responses emitted by the Mode S targets, and not elicited by the radar; for each target, associates its asynchronous responses with its synchronous response to the radar; a second step wherein the radar: based on the association, determines the response rate of each target by counting the number of synchronous and asynchronous responses received from the target per given time period; with the environment being divided into elementary space cells, determines the response rate per cell by counting the number of synchronous and asynchronous responses received by each target in each cell, the rate characterizing the density of Mode S interrogations per cell.

A system and method for cooperative aerial vehicle collision avoidance provides an ESA-based sensor network capable of high-resolution threat proximity measurements and cooperative and non-cooperative collision avoidance in the full spherical volume surrounding an aerial vehicle. The system incorporates a plurality of ESA panels onto the airframe where the conical scan volumes overlap leaving no gaps in spherical proximity coverage. The resulting received data is stitched together between the neighboring ESA panels and used to determine a position and vector for each threat aerial vehicle within range. The data is transmitted through a cooperative collision avoidance network to nearby aerial vehicles, and presented to the autopilot and flight crew to increase situational awareness. The system determines a maneuver for the aerial vehicle and a maneuver for the threat aerial vehicle based on relative maneuvering capabilities to maintain desired separation.

A system and method for cooperative aerial vehicle collision avoidance provides an ESA-based sensor network capable of high-resolution threat proximity measurements and cooperative and non-cooperative collision avoidance in the full spherical volume surrounding an aerial vehicle. The system incorporates a plurality of ESA panels onto the airframe where the conical scan volumes overlap leaving no gaps in spherical proximity coverage. The resulting received data is stitched together between the neighboring ESA panels and used to determine a position and vector for each threat aerial vehicle within range. The data is transmitted through a cooperative collision avoidance network to nearby aerial vehicles, and presented to the autopilot and flight crew to increase situational awareness. The system determines a maneuver for the aerial vehicle and a maneuver for the threat aerial vehicle based on relative maneuvering capabilities to maintain desired separation.

A landing zone landing assistance system for a rotary wing aircraft, the system includes a computer, an HMI for interacting with the pilot of the aircraft, an optical assembly provided with at least one optical sensor, a radar assembly provided with at least one radar detector and an inertial unit, wherein the computer is configured to implement the following steps: a first step (Step1) consisting in determining an optical image of the possible landing zone; a second step (Step2) consisting in determining the relative position of the landing zone with respect to said system in the terrestrial reference frame; a third step (Step3) consisting in determining a landing zone approach path; and a fourth step (Step4) consisting in supplying to the HMI a deviation between the position of the system and the approach path.

A landing zone landing assistance system for a rotary wing aircraft, the system includes a computer, an HMI for interacting with the pilot of the aircraft, an optical assembly provided with at least one optical sensor, a radar assembly provided with at least one radar detector and an inertial unit, wherein the computer is configured to implement the following steps: a first step (Step1) consisting in determining an optical image of the possible landing zone; a second step (Step2) consisting in determining the relative position of the landing zone with respect to said system in the terrestrial reference frame; a third step (Step3) consisting in determining a landing zone approach path; and a fourth step (Step4) consisting in supplying to the HMI a deviation between the position of the system and the approach path.

A radar system and method for sharing threat data is configured to communicate with other radar systems in surrounding aircraft and share threat specific data. Each radar system may be configured to a specific task according to the priorities of the aircraft and the capabilities of the surrounding aircraft; the gathered data is then shared with the surrounding aircraft such that each aircraft may commit longer dwell time to individual tasks while still receiving data for all of the potential tasks. The radar system may identify a fault and send a request for radar threat data to nearby aircraft. The radar system may receive such data within the operating band of the radar and allow continued operation.