Abstract:
A stress isolation technique for an accelerometer (10) of the type that has a reed (14, 80, 100, 120, 150) that includes a paddle (34, 84, 104, 134, 154), and flexures (36, 86, 106, 126, 156) connecting the paddle to an area of the support. The support includes one or more mounting pads (50-52, 94-96, 114, 130, 160) through which the reed is mounted. The area of the support adjacent to the flexures is divided into first (72, 90, 110, 142, 172) and second (74, 92, 112, 144, 174) portions, such that the flexures are connected to the first portion and such that the mounting pads are positioned solely on the second portion. The flexures are therefore isolated from stress coupled into the reed through the mounting pads.
Abstract:
A drive system (40) for providing different excitation voltages to the separate beams (16, 18) of a multiple beam vibrating transducer (12) is disclosed. In one embodiment of the invention an amplified voltage at the resonant frequency of a master beam (16) is amplified and applied to a secondary beam, to force the secondary beam (18) to vibrate at the resonant frequency and amplitude of the master beam (16) to force the transducer to resonate at the frequency of the master beam (16). Since the transducer (12) vibrates at the resonant frequency of one of the beams, the transducer energy losses to the adjacent mounting structure are reduced. This results in a higher transducer quality factor so that frequency shifts in the resonant frequency can be readily measured as changes in the parameter that the transducer (12) is intended to mionitor.
Abstract:
A method and apparatus for detecting amplitude compression in a guidance system utilizes a transmitting system (30) that transmits two pulses having a predetermined amplitude differential therebetween (26, 27, 28, 29) on each of a plurality of directional beams. The amplitudes of the pulses received from an individual one of the beams are compared (60, 62), and if the amplitude differential between the received pulses is different than the predetermined amplitude differential of the transmitted pulses, a signal indicative of receiver compression is generated (60, 62).
Abstract:
An accelerometer comprising a monolithic crystalline substrate (12), the substrate comprising a support (30), a proof mass (32), and a force transducer (40). The proof mass is connected to the support by one or more proof mass flexures (34) that permit the proof mass to rotate with respect to the support about a hinge axis (HA). One end of the force transducer is connected to the support, and the other end is connected to the proof mass by a transducer flexure (52). The transducer flexure has a thickness substantially less than the thickness of the transducer, such that when the proof mass rotates, the transducer rotates with respect to the proof mass about a transducer axis (TA) that passes through the transducer flexure. Preferably, the transducer axis is offset from the hinge axis in a manner so as to cancel nonlinearities in the force transducer, and the length of the proof mass along the pendulous axis (PA) is less than half the length of the transducer. Damping plates (20, 22) are positioned above and below the proof mass, and provide shock stops and damping.
Abstract:
A push-pull accelerometer in which both force transducers (30, 32) lie in a common plane. Thus, when implemented in a silicon micromachined device, both transducers can be fabricated from a single crystal layer (34), thereby producing transducers with closely matched common mode responses.
Abstract:
A vibrating beam force transducer that can be realized in a silicon micromachined device such as a micromachined accelerometer. The transducer includes a beam (18) having a longitudinal axis (16), and a drive circuit (24) electrically coupled to the beam for causing the beam to oscillate at a resonant frequency that is a function of a force applied along the longitudinal beam axis. The drive circuit provides an electrical current to the beam, and the beam, or a conductive portion (18) thereof, conducts the current along a path that includes an axial component parallel to the longitudinal axis. A magnetic field (B) is created intersecting the axial component, such that the electric current interacts with the magnetic field to produce a force that causes the beam to oscillate at the resonant frequency. In a preferred embodiment, the transducer has a double ended tuning fork configuration, and the current path extends along one beam and back along the other beam.
Abstract:
A technique is described for tailoring the configuration of electrodes (101-104) on a piezoelectric beam (100) such that the tendency of the beam to vibrate in a predetermined flexure mode is enhanced. The mode has a predetermined longitudinal strain versus longitudinal position profile (106). At least two electrodes are mounted on the beam, and the configuration of at least one electrode varies as a function of longitudinal position, such that when a voltage difference is applied between the electrodes, the longitudinal force produced by the electrodes, as a function of longitudinal position, approximates the longitudinal strain versus longitudinal position profile. The configuration may be varied by varying the width of the electrode or the position of the electrode on the underlying beam surface.
Abstract:
Apparatus and method for vertically aligning an acceleration sensitive axis of a gravity measurement device (10). The gravity measurement device (10) includes an accelerometer (68), which rotates about a gimbal shaft (62) within a gimbal frame (54). Gimbal frame (54) also rotates about an axis which is preferably oriented at right angle to gimbal shaft (62). A stepping motor (20) rotates accelerometer (68) about gimbal shaft (62) via antibacklash gear (30), idler gear (32), antibacklash gear (48) and drive shaft (50). In a similar fashion, a stepping motor (22) rotates gimbal frame (54). A controller (140) energizes motors (20, 22), to rotate the acceleration sensitive axis of accelerometer (68) until an output signal (170) indicates that the acceleration of gravity is zero. Once two such positions are located, a level reference plane is determined. Controller (140) then rotates accelerometer (68) 90° relative to the reference plane, thus aligning acceleration sensitive axis.
Abstract:
An instrument (10) is disclosed for an aircraft having a windshear warning system to vary the threshold alarm setting as a function of a thermodynamic property of the air and a function of local geographic and seasonal conditions. Specifically, a function generator (16) and other circuitry is disclosed. The output from the function generator (16) and other circuitry is then added to a fixed threshold acceleration signal to produce a threshold alarm signal (12) which has a value that is a function of the temperature of the air (11), in a basic embodiment.
Abstract:
A borehole survey system that utilizes strapdown inertial navigation techniques for mapping a borehole while the system probe (10) is continuously moved along a borehole (12) by means of a cable (14) that is wound on a cable reel (16). Signals representative of the acceleration of the probe (10) relative to the three axes of a probe body coordinate system (34) and signals representative of angular rotation of the probe (10) about the three axes of the probe body coordinate system are processed within the signal processor (24) to obtain signals that represent probe velocity and probe position in a level coordinate system (36) that is fixed in orientation relative to the geographic location of the borehole (12). Precise and continuous surveys are accommodated by correction of the level coordinate probe velocity signals and probe position signals with error correction signals that are based on the difference between inertially derived probe body coordinate position signals representative of the distance traveled by the probe (10) along the borehole (12) and a cable length signal that is derived from a cable measurement apparatus (26), which indicates the amount of cable (14) fed into or retrieved from the borehole (12). Error correction also is provided to correct for Coriolis effect, centrifugal acceleration and variations in the earth's gravitational field as a function of probe depth.