Abstract: A dent removing apparatus that utilizes piston technology along with the magnetism to remove dents includes a handle, a linear actuator, an interchangeable suction cup, and an interchangeable magnetized base. The handle allows the user to grasp the apparatus while the interchangeable magnetized base engages with the dent. A magnetized bottom rim of the interchangeable suction cup perimetrically positions around the dent and the interchangeable magnetized base and engaged with the surrounding surface area of the dent. Then the dent can be pulled or push to be even with the surrounding surface area through the linear actuator as the linear actuator can be manually, pneumatically, or electrically operated.

Abstract: A method for retrieving an unmanned aircraft is provided. The retrieval device may include a frame that supports a flexible material. The flexible material may form a receptacle portion shaped to receive the unmanned aircraft. The flexible material may absorb at least a portion of the energy exerted by the aircraft landing within the receptacle portion. Wheels may be connected to the frame to further control and absorb energy from the landing.

Abstract: A reconfigurable neural circuit includes a two dimensional array including a plurality of processing nodes, wherein each processing node includes a neuron circuit, a synapse circuit, a spike timing dependent plasticity (STDP) circuit, a weight memory for storing synaptic weights, the weight memory coupled to the synapse circuit, an interconnect fabric for interconnections to and from and between the neuron circuit, the synapse circuit, the STDP circuit, the weight memory, and between a respective node in the array and other processing nodes in the array, and a connectivity memory for storing interconnect routing controls coupled to the interconnect fabric.

Abstract: A pulse domain 1 to 2N demultiplexer has a (i) pair of N stage counters each of which is responsive to an incoming pulse train in the pulse domain, one of the counters being responsive to leading edges of the pulses in the incoming pulse train and the other one of the counters being responsive to trailing edges of the pulses in the incoming pulse train and (ii) a control logic responsive to the states through which the pair of counters count, the control logic including 2N gate arrangements, each of the 2N gate arrangements generating a output signal of the pulse domain 1 to 2N demultiplexer.

Abstract: The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process.

Abstract: A convolution circuit includes: a plurality of input oscillators, each configured to: receive a corresponding analog input signal of a plurality of analog input signals; and output a corresponding spiking signal of a plurality of spiking signals, the corresponding spiking signal having a spiking rate in accordance with a magnitude of the corresponding analog input signal; a plurality of 1-bit DACs, each of the 1-bit DACs being configured to: receive the corresponding spiking signal of the plurality of spiking signals from a corresponding one of the input oscillators; and receive a corresponding weight of a convolution kernel comprising a plurality of weights; output a corresponding weighted output of a plurality of weighted outputs in accordance with the corresponding spiking signal and the corresponding weight; and an output oscillator configured to generate an output spike signal in accordance with the plurality of weighted outputs from the plurality of 1-bit DACs.

Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demolding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.

Abstract: A circuit for detecting features in an image, the circuit including M time encoders, each time encoder having two inputs, Xi and Ti, where Xi is an ith element of an input vector X1 XM of the image and Ti is an ith element of a template vector T1 TM, and having an oscillatory output, wherein when the input vector X1 XM and the template vector T1 TM are more matched, the oscillatory outputs of the time encoders are more synchronized, and wherein when the input vector X1 XM and the template vector T1 TM are less matched, the oscillatory outputs of the time encoders are less synchronized.

Abstract: A frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector comprising the following structural elements a) a foot piece to be joined to the fuselage skin; b) a head piece; c) a web comprising one or more fitting-pieces for receiving said external loads and a plurality of X-shaped pieces joined by its ends to said foot piece and said head piece; and d) two connecting pieces of the ends of said foot piece and said head piece with the second sector of the frame.

Abstract: The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process.

Abstract: A method delaying a pulse domain signal using a time encoder circuit and a time encoder based beamformer method and apparatus for use in receiving and/or transmitting applications.

Abstract: An optimized structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs and at least one hinge fitting, as well as and an actuator fitting joined with the front spar. At least one rib is connected with the actuator fitting and it is arranged so as to define an oblique angle with the front spar. One or more ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff, so the same structural behavior of the control surface is achieved, but, with a reduced number of ribs, so that the weight of the control surface is reduced.

Abstract: A method of, and apparatus for, the processing analog data. The method includes the steps of: time encoding the analog data; setting weighting factors in an array of 1-bit DACs for processing the time encoded analog data; summing and filtering outputs of the array of 1-bit DACs; time encoding the filtered outputs of the outputs of the array of 1-bit DACs; and coupling the time encoded filtered outputs and analog input data into inputs of the array of 1-bit DACs.

Abstract: Horizontal tail plane of an aircraft which comprises a single torsion box which also comprises a front spar (1), a rear spar (2), an upper cover and a lower cover, ribs and two closing ribs (3), the front spar (1), the rear spar (2) and the upper and lower covers extending between said two closing ribs (3) and along the whole span of the horizontal tail plane in a symmetric layout with respect to the symmetry axis of the aircraft.

Abstract: A spike domain asynchronous neuron circuit includes a first spike to exponential circuit for emulating kinetic dynamics at a neuron input and converting voltage spikes into exponentials, a first adjustable gain circuit for emulating homeostatic plasticity coupled to the first voltage-type spike exponential output and having a first current output, a neuron core circuit coupled to the first current output for emulating a neuron core and having a spike encoded voltage output, a filter and comparator circuit coupled to the spike encoded voltage output and having a gain control output coupled to the first adjustable gain circuit for controlling a gain of the first adjustable gain circuit, and an adjustable delay circuit for emulating an axonal delay coupled to the spike encoded voltage output and having an axonal delay output.

Abstract: A retrieval device for an unmanned aircraft. The retrieval device may include a frame that supports a flexible material. The flexible material may form a receptacle portion shaped to receive the unmanned aircraft. The flexible material may absorb at least a portion of the energy exerted by the aircraft landing within the receptacle portion. Wheels may be connected to the frame to further control and absorb energy from the landing.

Abstract: A spike timing dependent plasticity (STDP) apparatus, neuromorphic synapse system and a method provide STDP processing of spike signals. The STDP apparatus includes a first leaky integrator to receive a first spike signal and a second leaky integrator to receive a second spike signal. An output of the first leaky integrator is gated according to the second spike signal to produce a first gated integrated signal and an output of the second leaky integrator is gated according to the first spike signal to produce a second gated integrated signal. The STDP apparatus further includes an output integrator to integrate a difference of the first and second gated integrated signals to produce a weighted signal. The system includes a synapse core and the STDP apparatus. The method includes integrating the spike signals, gating the integrated signals and integrating a difference of the gated integrated signals.

Abstract: A cortical neuromorphic network, system and method employ a plurality of neuromorphic nodes arranged in a network layer. The cortical neuromorphic network includes a neuromorphic node of the network layer in which the neuromorphic node includes a spike timing dependent plasticity (STDP) synapse and a neuromorphic neuron. The neuromorphic node is configured to receive a feedforward spike signal from selected ones of a plurality of input neurons of an input layer and to provide an output spike signal as a recurrent spike signal to the neuromorphic nodes of the network layer. A combination of the recurrent and feedforward spike signals is an excitatory spike signal of the neuromorphic node. The cortical neuromorphic system includes the neuromorphic nodes configured to operate according to a cycle and time slots of synaptic time multiplexing. The method includes receiving and weighting the excitatory spike signal using the STDP synapse and producing the output spike signal.

Abstract: A reinforcement structure for an opening in the primary structure of an aircraft, the structure comprising a skin, frame members which are transverse with respect to the flying direction of the aircraft, and stringers which are longitudinal with respect to the flying direction of the aircraft. The reinforcing structure includes a perimetral reinforcing element situated along the edge of the opening and reproducing the geometrical form thereof; at least one pair of transverse reinforcing elements arranged on both transverse sides of the opening; and at least one pair of longitudinal reinforcing elements arranged on both longitudinal sides of the opening.

Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.