Provided is a circuit abnormality diagnosis device capable of simply and easily diagnosing a circuit abnormality, a current generating device including the circuit abnormality diagnosis device, a deployed object ejection device for a flight object including the current generating device, an airbag device for a flight object including the current generating device, and a cutting device for a flight object including the current generating device.

A circuit abnormality diagnosis device 110 includes a calculation unit 1, an inspection power supply 2, a rectifier element 3, overcurrent preventing resistors 4 and 5, a voltage amplification unit 6, a voltage reading unit 7, and a light emitting unit 8, and performs a circuit abnormality diagnosis at a preset time (including the time of initial mounting) or every predetermined time. The circuit abnormality diagnosis device 110 diagnoses (determines) that a case where a voltage value is within a range of a first voltage value V.sub.1 or more and a second voltage value V.sub.2 or less, which is set in advance as a range of voltage values indicating that a circuit is normal, is a normal state, a case where the voltage value is less than the voltage value V.sub.1 is a short-circuit state in which the circuit is short-circuited, and a case where the voltage value is higher than the voltage value V.sub.2 is a disconnection state in which the circuit is disconnected.

An experimental bench for an unmanned aerial vehicle (UAV) power system and avionics equipment, which relates to the technical field of UAV test, comprising a support component, a power system load-bearing component, an avionics equipment load-bearing component, a jacking component and a roller component. A plurality of power system load-bearing components are provided, and are fixedly arranged on the support components, respectively, and each power system load-bearing component is configured to carry the power system of a UAV; the avionics equipment load-bearing component is fixedly arranged on the support component, and the avionics equipment load-bearing component is configured to bear the avionics equipment of the UAV; the output end of the jacking component is fixedly connected to the bottom end of the support component.

An apparatus including a frame forming an interface device configured for connection to a test chassis, and at least one interface connector coupled to the frame, the at least one interface connector corresponding to connectors of a unit under test, the interface device being configured for insertion through one or more sealable apertures of an environmentally protective chassis that houses the test chassis, and coupling to an interface device seating surface of the environmentally protective chassis without any intervening environmental interface or environmental interface plane located between the interface device seating surface and the test chassis, wherein the frame forming the interface device includes a first end plate configured with electrical connectors and mechanical attachment members configured to align and attach a circuit card to the interface device.

The present invention belongs to the technical field of aviation electrics and electric power, and provides an aircraft grid phase angle tracker based on nonlinear active disturbance rejection, which is used to estimate the grid phase angle on AC side of an aircraft grid. A embedded generator in the aircraft grid is arranged inside a compressor of an aviation gas turbine engine, and the embedded generator is directly coupled with the aviation gas turbine engine so that the AC frequency of the embedded generator varies with the speed of the aviation gas turbine engine. The present invention applies the nonlinear active disturbance rejection technology to the phase angle tracking of the more electric aircraft grid, is simple in operation and high in accuracy, and can realize high-accuracy tracking of the grid phase angle. The method has certain extensibility and can be extended to other fields.

A method for measuring the hardware and operational state of a dual-circuit solenoid valve including first and second coaxial coils each associated with a circuit is disclosed. The method includes the steps of injecting a sinusoidal current into the first coil; measuring the voltage induced across the terminals of the second coil; and plotting at least one curve of a first magnitude proportional to the measured induced voltage as a function of a second magnitude proportional to the injected sinusoidal current.

The invention relates to a method for detecting events by reflectometry in an electrical line of an avionic system, said line being fed with an AC voltage at a first frequency (f1), said AC voltage being sinusoidal and composed of a succession of alternate half-periods, said method comprising a step of injecting a reflectometry signal into the network, the reflectometry signal having a second frequency (f2) higher than the first frequency (f1); wherein the injecting step is synchronized with the AC voltage, the injecting step being carried out by injecting the reflectometry signal into the network during an injection duration (ti) comprised between the start and end of a half-period (t1) of the AC feed voltage.

In accordance with at least one aspect of this disclosure, a system can include a positive input line configured to connect between a voltage input and a load, and a negative input line configured to connect between the voltage input and the load. A logic module can be operatively connected to and/or configured to detect a fault (e.g., a short circuit) in either of the positive input line or the negative input line 104 between the voltage input and the load.

A method for monitoring insulation in a motor drive circuit configured to convert DC power from a power source to AC power to drive a motor. The method includes boosting a DC link voltage of an inverter of the motor drive, isolating the motor drive circuit from the power source; performing at least one isolation test by providing a current path through components of the motor drive and preferably a motor connected to the output of the inverter to be tested; and monitoring the current during each isolation test to detect partial discharge or excessive leakage from the current path, thereby indicating that there exists defects in the insulation in the current path.

Disclosed is a detector 10 using a liquid spray 2000 for detecting electrical faults or shorts with the detector including a body 100 having an interior 120; a hose or pipe 130 fluidly connected to interior 120; a trigger valve 140 operatively connected to hose 130; a conductor 200 attached to detector 10; and/or a pump 110 fluidly connected to interior 120. In various embodiments the detector 10 can cause liquid spray 2000 to be sprayed on a subregion of an item such as a remotely operated vehicle to create a closed electrical circuit through the liquid spray and the conductor in the detector.

Systems and methods relate to electric propulsor fault detection. An exemplary system includes at least a first inverter configured to accept a direct current and produce an alternating current, a first propulsor, a first motor operatively connected with the first propulsor and powered by the alternating current, and at least a noise monitoring circuit electrically connected with the direct current and configured to detect electromagnetic noise and disengage the at least an inverter as a function of the electromagnetic noise.