Airbus Defence and Space

Cognitive radiocommunication system for aerial platforms comprising: an antenna system (1) including radiating elements (5); radiofrequency transmitter-receiver unit (2) configured for receiving and transmitting radio beams (6/6'). The incident radio beams are managed by a cognitive signal processor (4), which includes a spectrum sensing module (12) for detecting and classifying signals in the received beams (6); a spectrum prediction module (13) for finding trends in the spectrum, and a spectrum decision module (14) for allocating resources to the cognitive network nodes. The radiocommunication module may also comprise a sharing module (15) use to exchange information among users inside the network. The processor also includes a cognitive transceiver (16) to generate a transmission beam with payload user data (11') using the decision taken, and to receive the payload user data (11) inside the received signals (10).

The present disclosure relates to a flight control method for controlling a formation of a plurality of aircraft, comprising the steps of: determining an initial formation state of the plurality of aircraft; establishing a final formation state of the plurality of aircraft; generating a plurality of candidate trajectories for each aircraft from an initial position of the respective aircraft to at least one end position in the final formation state; applying at least one constraint to the plurality of candidate trajectories for each aircraft to provide a reduced trajectory set, wherein the at least one constraint comprises an aircraft-specific parameter; selecting a final trajectory set, each comprising a trajectory from each reduced trajectory set of the corresponding aircraft, such that the final trajectory set is collision-free; and providing the respective trajectory according to the final trajectory set to each corresponding aircraft.

A method of detecting moving objects (O) with a radar detection system (2) for a vehicle (1), such as a satellite, in particular for space debris detection, a corresponding computer program (11), computer-readable data carrier (12), a control module (6), a radar detection system (2) and a vehicle (1), in particular a satellite, are provided, the method comprising the step of emitting a radar signal containing a pulse train sequence (W) comprising at least two pulse trains (V) of radar pulses (P) having different pulse repetition frequencies (PRF).

The present invention provides an aircraft (100), having a fuselage (110), a wing assembly (120), a propulsion device (130), and two tail booms (140), each comprising a stem (141) and a stabilizing surface (142), wherein the stabilizing surfaces (142) of the tail booms (140) are each arranged symmetrically with respect to the respective stem (141) of the tail boom (140), wherein the stabilizing surfaces (142) of the tail booms (140) are arranged at an angle to one another in such a way that upper edges of the stabilizing surfaces (142) have a smaller spacing than lower edges of the stabilizing surfaces (142), and wherein each of the stabilizing surfaces (142) has a tilting device (143) for controlling the aircraft (100).

The present invention provides a method for calibrating a detector device under test, DUT, (2) with respect to linearity, comprising a) irradiating (M1) the DUT (2) with a first optical beam (31) and a second optical beam (41) for a predetermined time period, wherein the first optical beam (31) has a predetermined constant first optical power (32), and wherein the second optical beam (41) is an amplitude modulated optical beam, b) obtaining (M2) a detection signal (21) from the DUT (2), c) repeating (M3) steps a) and b) for a plurality of different predetermined first optical powers (32), d) calculating (M4) a derivative nonlinearity curve of the DUT (2) based on the obtained detection signals of the plurality of first optical powers (32), and e) providing (M5) a calibration curve to transform measured digital values into a linearized scale of optical power on the DUT (2) based on the calculated derivate transfer function (f') of the DUT (2). Further, the present invention provides a corresponding calibration device for calibrating a detector device (2) under test and an optical payload (102) for a satellite or an aircraft.

The present disclosure relates to a method M, in an aircraft guidance and/or navigation system S, to guide an aircraft AC towards or from a landing site LS using measurements, onboard the aircraft, of one or more unique artificial magnetic fields MF1, MF2, MFN assigned to a vicinity V of the landing site. The present disclosure also relates to a magnetic ground infrastructure MGI in the aircraft guidance and/or navigation system S, to guide the aircraft AC towards or from the landing site LS, the magnetic ground infrastructure comprising one or more emitters E1, E2, EN assigned to the vicinity V of the landing site, each emitter being adapted to generate a respective unique artificial magnetic field MF1, MF2, MFN. The present disclosure also relates to the aircraft AC in the aircraft guidance and/or navigation system S, to guide the aircraft towards or from the landing site LS, the aircraft comprising one or more magnetometers MM1, MM2, MMN adapted to detect the one or more unique artificial magnetic fields MF1, MF2, MFN assigned to the vicinity V of the landing site; and a navigation system NS adapted to calculate a relative or an absolute position of the aircraft in relation to the landing site, based on detection result of the one or more magnetometers.

A new method uses a nitrogen monoxide (NO) sensor 10, which is arranged in an exhalation channel 3 of a breathing mask 1, which comprises a pressure ventilation device, an acceleration sensor 20, a ventilation pressure sensor 30, which is arranged in a breathing air channel 2 of the breathing mask 1, and comprises the following steps: • a computer calculates an individual, unadjusted stress tolerance rating and uses for this purpose the measured value of the NO sensor 10 together with historical measured values and associated, historical calculation values, • the computer calculates out the influence of the acceleration acting on the fighter pilot and the influence of the pressure ventilation acting on the fighter pilot and uses for this purpose measured values of the acceleration sensor 20 and of the ventilation pressure sensor 30 together with historical measured values of the acceleration sensor 20 and of the ventilation pressure sensor 30 and associated historical calculation values while obtaining an individualized, adjusted stress tolerance rating, • wherein the historical measured values and the historical calculation values are stored in the memory and are data of the fighter pilot.

Computer implemented method for training a feed-forward deep learning model intended to the detection and instance segmentation of objects, comprising the steps of: inserting (S1) a gradient reversal layer (GRL) after a hidden layer of the deep learning model, inserting (S2) a domain classifier layer (DCL) after the gradient reversal layer (GRL); introducing (S3) a set of input values (I) of training data into an input layer of the deep learning model; obtaining (S4) a set of output values (O) in response to said input values (I); calculating (S5) a loss function of the last hidden layer of the deep learning model, calculating (S6) the gradient of the loss function; propagating backwards the loss function and repeating steps (S5) and (S6) for each hidden layers and adjusting (S7) the weight of each hidden layer, so as to minimize the gradient of the loss function.

Provided is a method (200) for supporting positioning services in a communication system, and a corresponding apparatus (400). The method comprises generating (210), by at least one transmitter (110, 120), at least one reference signal; allocating (220), by the at least one transmitter (110, 120), the at least one reference signal over a bandwidth, wherein the at least one reference signal is muted in frequency domain according to a frequency muting pattern; and transmitting (230), by the at least one transmitter (110, 120), the allocated at least one reference signal to a receiver (110, 120).

The present invention provides a method for calibrating a detector device (2) under test, comprising a) emitting a number of n first laser pulses (P2-P4) by a first set (S1) of corresponding n laser sources (3a-d) of a plurality of laser sources (3a-d) in a first time slot (t1) and a number of m second laser pulses (P1) by a second set (S2) of m laser sources (3a-d) of the plurality of laser sources (3a-d) in a second time slot (t2) different from the first time slot (t1), wherein n ≥ 1, m ≥ 1, and n + m ≥ 3, wherein a ratio of n and m is defined as a predetermined pulse ratio n/m, wherein the first laser pulses (P2-P4) and the second laser pulses (P1) have a predetermined pulse energy; b) combining the first set (S1) of n laser pulses and the second set (S2) of m laser pulses to obtain a first combined laser pulse (PC1) in the first time slot (t1) and a second combined laser pulse (PC2) in the second time slot (t2); c) directing the first and second combined laser pulses (PC1, PC2) onto a detector (21) of the detector device (2); d) detecting the first combined laser pulse (PC1) in the first time slot (t1) and the second combined laser pulse (PC2) in the second time slot (t2) by the detector device (2) to provide corresponding first and second electric signals (61, 62); e) repeating steps a) to d) by regrouping the plurality of laser sources (3a-d) into a different first set (S1) of n laser sources (3a-d) and a different second set (S2) of m laser sources (3a-d) through all permutations (A-D) of the plurality of laser sources (3a-d) by keeping the predetermined pulse ratio n/m; and f) averaging each of the detected first and second electric signals (62) of all permutations (A-D) to obtain an averaged first electric signal (61') and an averaged second electric signal (62') indicative of the response of the detector device (2) for the predetermined pulse ratio n/m. Further, the present invention provides a corresponding calibration device for calibrating a detector device (2) under test.