Abstract: A human-portable MEMS azimuth sensing unit and method that determines the azimuth of a target. There is a spinning support structure, with at least a gyroscope carried by the support structure. The gyroscope has an input axis and an output signal. There is an angle resolver that measures the spin angle of the support structure relative to a reference direction and that has an output signal. Circuitry determines the target azimuth based on the phase difference between the output signals of the gyroscope and the angle resolver. The phase difference can be based on the time between zero crossings of the sinusoidal gyro and angle resolver signals. An accelerometer can also be carried by the support structure, in which case its output can be used to level the unit.

Abstract: Inertial Measurement Units based on integrated designs to reduce alignment and assembly costs. Integration also leads to performance improvement, increased miniaturization and simplification as well as reduced cost. Also disclosed are gyroscopes and accelerometers that are identical, yet by their mechanization, can be made to act as separate sensors. Miniaturization and simplification is improved by combining instruments that can share a common member. Savings in space and complexity are also possible in the electronics when elements are shared.

Abstract: The planarization of inductive components by reducing standard coiled designs to single turn, open ended designs from which the required parameters are obtained by scaling the length. Single turn designs having magnetic material encircling the conductors along their full length enable the thinnest form. The single turn, open ended form also enables the inductive component to be routed according to any shape in the plane or on any conformal surface. The single turn inductors do not need to coil hence there is no overlap necessary in the plane. The planar form allows integration of inductive components with integrated circuits. These inductive components can be embedded in other materials. They can also be fabricated directly onto parts.

Abstract: Disclosed is a Coriolis Oscillating Gyroscopic instrument, comprising: a Double Ended Tuning Fork (DETF) having two stems and two tines; a Torque Summing Member (TSM) rigidly coupled to the DETF stems; drives located at least partially on the TSM for vibrating the tines sinusoidally in opposition along a first axis, the tines' motion having a constant amplitude, a frequency and a phase; a case; a plurality of flexures connecting the TSM to the case, to allow the TSM and the DETF to rotationally oscillate together relative to the case about a second axis transverse to the first axis; and a sensor and associated instrumentation for resolving rotation of the TSM relative to the case.

Abstract: This invention describes a technique for measuring the peak amplitude and phase of an oscillating member without using any external precision references other than stable precision frequencies. The technique relies upon stable reference dimension of the oscillating member and stable dimensions of a stationary system which the member is oscillating with respect to. The technique uses a stable precision crystal clock oscillator to measure the time at which the oscillating member arrives at certain reference angles. The reference angles may be established on the member or by interferometry, with respect to sensors on a stationary member. Using inputs from the sensors, a precision clock, and counters the system determines the period of oscillation of the vibrating member and the phase of the maximum excursions of the vibrating member based on the time required for the oscillating member to move through the reference angles established on the reference member.

Abstract: A tuned flexure accelerometer, comprising, a housing; a gimbal coupled to the housing for oscillation about a gimbal oscillation axis; and a reference mass coupled by one or more pivots to the gimbal to allow pivoting motion of the reference mass relative to the gimbal about a pivot axis which is transverse to the gimbal oscillation axis, the one or more pivots having an effective elastic restraint. The gimbal is oscillated about its oscillation axis, to thereby induce on the one or more pivots an oscillating negative elastic restraint, to reduce the effective elastic restraint of the pivots.