A co-prime coded DDM MIMO radar system, apparatus, architecture, and method are provided with a reference signal generator (112) that produces a transmit reference signal; a plurality of DDM transmit modules (11) that produce, condition, and transmit a plurality of transmit signals over which each have a different co-prime encoded progressive phase offset from the transmit reference signal; a receiver module (12) that receives a target return signal reflected from the plurality of transmit signals by a target and generates a digital signal from the target return signal; and a radar control processing unit (20) configured to detect Doppler spectrum peaks in the digital signal, where the radar control processing unit comprises a Doppler disambiguation module (25) that is configured with a CPC decoder to associate each detected Doppler spectrum peak with a corresponding DDM transmit module, thereby generating a plurality of transmitter-associated Doppler spectrum peak detections.

A surface-based transmitter system for assisting determination of vehicle location is presented. The system comprises a set of radio frequency (RF) transmitter nodes that, when deployed at different respective locations, are configured to output a sequence of respective RF pulses with a predefined inter-pulse delay between each pair of consecutive RF pulses in the sequence, wherein the pre-defined inter-pulse delay is longer than 1 microsecond. The set of RF transmitter nodes include at least a first RF transmitter node, a second RF transmitter node, a third RF transmitter node, and a fourth RF transmitter node, which are configured to output a first RF pulse, a second RF pulse, a third RF pulse, and a fourth RF pulse, respectively, of the sequence of RF pulses.

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 method for monitoring the take-off and/or landing procedure of an aircraft (1), in particular for an electrical, vertical take-off and landing aircraft (1), in which a monitoring region of a take-off and landing site (2) is monitored by at least one microphone (4, 5) of a monitoring station to detect sound emission data of an aircraft (1) taking off or landing as it approaches or departs and the detected sound emission data are transmitted from the monitoring station to an evaluation unit. The detected sound emission data are evaluated by the evaluation unit by comparing the detected sound emission data to characteristic sound emission data.

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.

An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.

An instrument landing system (ILS) is described. The ILS comprises a plurality of antennas and a plurality of antenna radio units (ARUs). Each ARU of the plurality of ARUs operates to generate a modulated RF signal provided to a different one of the plurality of antennas for transmission. The ILS further comprises a central processing unit that operates to control the ARUs to adjust synchronization between the modulated RF signal provided by the ARUs to the plurality of antennas for transmission.

An imaging method using a doppler radar wherein the pointing direction in transmission (d.sub.ei) is modified from recurrence to recurrence; each detection block of duration T comprises a periodic repetition of a number C of pointing cycles, each of these cycles comprising a number P of recurrences, the set of these P recurrences covering the D.sub.e pointing directions (d.sub.ei) of the set; the order of the pointings is modified in a pseudo-random manner from pointing cycle to pointing cycle during a same detection block so as to create an irregular time interval between two pointings in a same direction; at least one beam is formed in reception on each recurrence in a direction included in the transmission-focused angular domain in the pointing direction corresponding to the recurrence.

A landing guidance system for an aircraft is described and includes at least one receiver for installation on the aircraft, the at least one receiver configured to receive signals emitted by a plurality of emitters associated with a landing area; and a processing system for processing the received signals to determine at least one of a location, a distance, an orientation, a configuration, and a geometry of the landing area relative to the aircraft.

A receiver includes an RF module to receive and down convert multiple types of RF signals received from at least one antenna; a communication unit configured to communicate signals with at least one external device; and a processing unit communicatively coupling the radio frequency module with the communication unit. Processing unit receives operation mode selection. When first operation mode is selected, processing unit receives first input signal from antenna via RF module (the first input signal including ILS signal and/or VOR signal) and outputs first output signal based on first input signal to external device. When second operational mode is selected, processing unit receives second input signal from antenna via radio frequency unit (second input signal including AIS signal including data regarding a current location of remotely located transmitting device) and outputs second output signal based on second input signal to external device.