9 results about "Signal Conditioner" patented technology

The application discloses a flat valve repairing device, which comprises a fixing device, a valve cover disassembling device, a valve seat disassembling device, a turnover device, a valve cover fastening device, a packing sealing device and an ultrasonic cleaning device. The fixing device is used for fixing the flat valve; the valve cover disassembling device is used for disassembling the valve cover of the flat valve; the valve seat disassembling device is used for disassembling the valve seat; the turnover device is used for rotating the flat valve; the valve cover fastening device is used for clamping the valve cover; the packing sealing device is used for sealing the packing into the valve cover of the flat valve; and the ultrasonic cleaning device is used for cleaning the disassembled parts. The application further discloses an automatic control system of the flat valve repairing device, which realizes the automatic disassembling, assembling and packing sealing of the flat valve through an industrial control touch screen, a PLC controller, an A / D converter, a signal conditioner, a circuit driver and a power component driver. The application realizes the automatic operation of the disassembling and packing sealing of the flat valve, has high working efficiency and low labor intensity, and is suitable for all scenes in which the flat valve needs to be disassembled.

This invention provides a spacecraft interface force extraction and force limit testing method based on the least squares method, applicable to a spacecraft vibration testing system. The testing system includes a vibration table, an extended table surface or horizontal slide, test fixtures, a signal conditioner, a vibration controller, a power amplifier, a vibration table oil pump, a cooling unit, and an external circulating water system. The testing method comprises fourteen steps. This invention's method analyzes a wide frequency range, reduces the cost of spacecraft force limit testing, meets the engineering application requirements for quantifying interface forces, effectively mitigates overtesting in spacecraft vibration testing, and ensures the safety of spacecraft products and equipment operation.

A turbo-boost controlled intake system is disclosed that provides a driver of a vehicle with greater control over vehicle performance. The turbo-boost controlled intake system includes a control module that is coupled with an aircharger air intake. The control module instructs an electronic control unit of the vehicle to increase manifold pressure to a higher level before releasing the pressure through a waste gate so as to provide a greater power output of the engine. The turbo-boost controlled intake system further includes a wiring harness and a signal adjuster. The wiring harness couples the control module with a turbo inlet pressure sensor, a manifold absolute pressure sensor, and an electronic control unit of the vehicle. The signal adjuster includes a rheostat that enables manual adjustment of the power output of the engine.

The application provides a wide-range quasi-static six-dimensional force measuring device for a spacecraft, comprising four force sensors, a set of upper and lower mounting plates, a charge amplifier and a data acquisition instrument, the four force sensors are installed between the upper mounting plate and the lower mounting plate and are distributed in a rectangular diagonal manner, the force sensors are connected with the charge amplifier, the charge amplifier outputs three-axis resultant force and resultant moment to the data acquisition instrument according to the measurement signals of the force sensors; the charge amplifier is a Kistler multi-channel signal conditioner, which is specifically used for calculating and outputting corresponding resultant force and resultant moment according to the measurement signals input by the force sensors. In this way, the application realizes wide-range wide-band quasi-static force measurement of the spacecraft, can obtain interface force and moment information at the connecting point of the spacecraft, has the advantages of wide test frequency band, high eccentricity test precision and low cost.

This invention discloses a self-zeroing fluxgate current sensor, belonging to the field of current sensor technology, aiming to solve the problem of zero-point bias error caused by the asymmetry of amplitude or phase of the two excitation signals in existing fluxgate current sensors. It includes an excitation signal generation circuit, two excitation cores and coils, an adder, an adjustable bandpass filter, an amplitude adjustment branch, a phase adjustment branch, a zero-adjustment controller, and a signal conditioner. The amplitude adjustment branch extracts the amplitude matching error of the two excitation induction signals, the phase adjustment branch extracts the phase deviation of the two excitation induction signals, the adjustment controller calculates the gain adjustment value and the phase adjustment value, and the signal conditioner uses the gain adjustment value and the phase adjustment value to adjust the gain and phase of one of the excitation drive signals in a closed loop, making the two excitation drive signals equal in amplitude and opposite in phase, directly eliminating the amplitude error and phase error from the excitation source, realizing mutual cancellation of the fundamental wave and odd harmonics, and fundamentally suppressing zero-point bias.

The technology disclosed teaches a system and methods for end-to-end self-calibration of a channel emulator, wherein the channel emulator includes at least one channel emulator signal chain and at least one integrated parallel calibration signal chain. The channel emulator signal chain further includes an input signal, a first signal conditioner, a first analog-to-digital converter, a baseband processor, second signal conditioner, and an output. The integrated parallel calibration signal chain further includes a sequence generator, wherein the sequence generator is configured to generate a pseudo-random sequence upon which a calibration analysis signal is overlayed. On the supplying side, the sequence generator is coupled to a second digital-to-analog converter for supplying the calibration analysis signal to be processed by the channel emulator signal chain. On the evaluating side, the sequence generator is coupled to a comparator for evaluating results of the processed calibration analysis signal.