| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Fluid jet deflection-type instrument with jet buoyancy control | US3631729D | 1969-06-05 | US3631729A | 1972-01-04 | MOORE ALVIN G |
| An instrument wherein the deflection of a fluid jet induced, for example, by the angular movement of the instrument produces a signal proportional to the deflection; and particularly, such an instrument having means for adjusting the temperature of the fluid to control the buoyancy of the jet relative to the surrounding fluid. This expedient is used, for example, to balance the density of the jet fluid and the surrounding fluid to neutralize the buoyancy of the jet and thereby eliminate jet deflection induced by acceleration, or to induce a predetermined temperature differential between the jet fluid and the surrounding fluid and thus through induced buoyance, to render the instrument responsive to acceleration.
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| 62 | Fluid jet deflection type instrument | US3626765D | 1969-06-05 | US3626765A | 1971-12-14 | MOORE ALVIN G; SCHUEMANN WILFRED C |
| AN INSTRUMENT WHEREIN THE DEFLECTION OF A FLUID JET, INDUCED FOR EXAMPLE BY THE ANGULAR MOVEMENT OF THE INSTRUMENT, PRODUCES A SIGNAL PROPORTIONAL TO THE DEFLECTION, AND PARTICULARLY SUCH AN INSTRUMENT THAT IS SUBSTANTIALLY SELF-CONTAINED TO PROVIDE A CLOSED FLUID CIRCUIT THAT IS RELATIVELY INSENSITIVE TO TRANSIENT TEMPERATURE DIFFERENTIALS AND IN WHICH THE OVERALL DIMENSIONS OF THE INSTRUMENT HAVE BEEN MINIMIZED.
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| 63 | Jet adjustment means for fluid jet deflection type instruments | US3581578D | 1969-06-05 | US3581578A | 1971-06-01 | SCHUSEMANN WILFRED C |
| An instrument wherein the deflection of a fluid jet, induced for example by the angular movement of the instrument, produces a signal proportional to the deflection, and particularly, such an instrument having means for adjusting the jet into a centered condition relative to the sensing means. The means herein disclosed comprises a plurality of adjusting elements such as setscrews that are turned down to provide an obstruction in the flow path of the fluid to the jet nozzle, the adjusting elements being located adjacent to and symmetrically about the nozzle inlet.
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| 64 | Impact and sound analysis for golf equipment | US13839231 | 2013-03-15 | US09217753B2 | 2015-12-22 | Arthur Molinari; Nicholas A. Leech |
| Golf performance and equipment characteristics may be determined by analyzing the impact between a golf ball and an impacting surface. In some examples, the impacting surface may be a golf club face. The impact between the golf ball and the surface may be measured based on sound and/or motion sensors (e.g., gyroscopes, accelerometers, etc.). Based on motion and/or sound data, various equipment-related information including golf ball compression, club head speed and impact location may be derived. Such information and/or other types of data may be conveyed to a user to help improve performance, aid in selecting golf equipment and/or to insure quality of golfing products. | ||||||
| 65 | Impact and Sound Analysis for Golf Equipment | US13838690 | 2013-03-15 | US20140278207A1 | 2014-09-18 | Jeffrey Hadden; Douglas A. Thornton; Bradley C. Glenn |
| Golf performance and equipment characteristics may be determined by analyzing the impact between a golf ball and an impacting surface. In some examples, the impacting surface may be a golf club face. The impact between the golf ball and the surface may be measured based on sound and/or motion sensors (e.g., gyroscopes, accelerometers, etc.). Based on motion and/or sound data, various equipment-related information including golf ball compression, club head speed and impact location may be derived. Such information and/or other types of data may be conveyed to a user to help improve performance, aid in selecting golf equipment and/or to insure quality of golfing products. | ||||||
| 66 | Oscillation of vibrating beam in a first direction for a first time period and a second direction for a second time period to sense angular rate of the vibrating beam | US11057324 | 2005-02-11 | US07174785B2 | 2007-02-13 | Robert E. Stewart |
| An apparatus in one example comprises a vibrating beam, a first drive component, and a second drive component. The first drive component for a first time period oscillates the vibrating beam in a first direction to sense angular rate of the vibrating beam. The second drive component for a second time period oscillates the vibrating beam in a second direction to sense angular rate of the vibrating beam. | ||||||
| 67 | Magnetohydrodynamic (MHD) actuator sensor | US11239283 | 2005-09-30 | US07171853B1 | 2007-02-06 | Darren R. Laughlin |
| An MHD sensor/actuator is provided for generating torque as well as sensing angular displacements around a sense/torque axis. A column of conductive liquid which rotates within a circumferential channel having an inner circumferential surface and outer circumferential surface provides an inertial proof mass, the relative motion of which within the channel generates a torque or represents a sensed displacement about the common axis of the circumferential channel. According to certain embodiments, a cylindrical column of magnets are located coaxially with the circumferential channel to produce a radially oriented magnetic field which is perpendicular to the common axis. According to other embodiments, a magnetic ring is provided coaxially with the circumferential channel to produce a magnetic field in the direction of the common axis. | ||||||
| 68 | MHD sensor for measuring microradian angular rates and displacements | US09302949 | 1999-04-30 | US06173611B1 | 2001-01-16 | Darren R. Laughlin |
| An angular rate sensor which measures submicroradian angular displacements. An MHD sensor is provided having a cylindrical column of conductive fluid, centered about a measurement axis. The magnetic field for the device is generated from permanent magnets and a shunt structure which produces radial magnetic field components through the cylindrical conductive fluid channel. The first electrode contacts an upper end of the cylindrical conductive fluid channel, and a second electrode contacts a lower end of the cylindrical conductive fluid channel. Current produced as a result of an electrostatic potential generated in response to the rotation of the device, flows through a center electrode connecting the first and second electrodes. A transformer winding surrounding the center electrode produces an amplified rate signal from the current flowing between the first and second electrodes. | ||||||
| 69 | Gyroscope noise reduction and drift compensation | US674389 | 1996-07-01 | US5795988A | 1998-08-18 | Pei-hwa Lo; Peter Halatyn; Eric Geoca; James B. Archibald |
| A low-cost gyroscope can provide an output approaching the accuracy of more precise instruments by processing the gyroscope output signal. First, a calibration algorithm develops a set of coefficients to predict drift. Second, an adaptive operational algorithm updates the coefficients during periods of inactivity and filters out high and low frequency noise components. An accurate, low-cost, rugged aiming device for a weapon can be realized with a simple, relatively-inexpensive gyroscope by utilizing the foregoing algorithms. | ||||||
| 70 | Active magnetohydrodynamic rate sensor | US674778 | 1996-07-03 | US5665912A | 1997-09-09 | Darren R. Laughlin |
| A magnetohydrodynamic sensor having an annular or circular sense channel containing a conductive liquid proof mass. A radial flow is introduced into the annular channel which, in response to rotation of the device, produces a coriolis force and resulting circumferential velocity of the fluid. An electromagnetic winding produces an alternating electromagnetic field directed perpendicular to the annular channel. First and second electrodes sense a time varying electric potential induced between the center of the annular channel and the circumference of the annular channel. The time varying electrical potential is proportional to the strength of the time varying electric field and rotational velocity of the channel with respect to said proof mass. The transformer connected to the electrodes provides for amplification of the signal representing the rotational velocity of the channel with respect to the proof mass. Synchronous detection of the alternating voltage produced by the electrodes permits very small angular velocities to be measured. | ||||||
| 71 | Gas rate sensor for detecting horizontal angular velocity | US384910 | 1995-02-07 | US5641903A | 1997-06-24 | Sukeyuki Shinotuka; Takashi Hosoi; Hiroshi Yamakawa |
| A gas rate sensor comprising a sensor body, a pump control device and a resistive bridge circuit. Semiconductor substrates are accurately photoengraved by semiconductor fabrication techniques to integrally form a pair of heat-generating and heat-sensitive resistive elements, a gas passageway, a pump casing, and other components in the sensor body. The pump control device controls a piezoelectric pump for creating a gas flow. The resistive bridge circuit is composed of the aforementioned resistive elements and a pair of reference resistors. The pump control device sets the gas flow rate to a given value to detect only the angular velocity acting in the direction of yaw. The angular velocity can be detected accurately with high sensitivity. | ||||||
| 72 | Gas flow type angular velocity sensor | US390875 | 1995-02-17 | US5553497A | 1996-09-10 | Mizuho Doi; Tomoyuki Nishio; Nobuhiro Fueki |
| A gas flow type angular velocity sensor which is capable of reliably sensing an angular velocity while accurately controlling the working gas flow with temperature compensation by using a pair of heat wires as a gas flow sensor without providing any additional gas flow sensor in the sensor body wherein an angular velocity sensing bridge circuit is provided at its current supply source with a temperature compensating circuit connected in series which temperature compensating circuit is composed of a pair of series or parallel connected resistance elements, one of which is a thermosensitive resistance element disposed in a gas path and the other of which is a reference resistance element disposed outside the gas path. | ||||||
| 73 | Gas flow type angular velocity sensor | US40937 | 1993-03-31 | US5385046A | 1995-01-31 | Hiroshi Yamakawa; Masayuki Ikegami; Tsuyoshi Hano |
| An angular velocity sensor of the type wherein a flow of gas forced by a pump into a gas path in the sensor body through a nozzle hole and directed toward a pair of thermosensitive resistance elements provided in the gas path is deflected by the action of an angular velocity and the deflection of the gas flow is sensed by the thermosensitive resistance elements, and which is further provided with a thermostatically-controlled gas path which is heated in order to maintain the gas flow at a constant temperature to avoid the effect of ambient temperature variations. The sensor also is provided with a gas path for absorbing pulsations of the gas flow caused by pumping operations. | ||||||
| 74 | Superconducting Josephson junction gyroscope apparatus | US527963 | 1990-05-23 | US5058431A | 1991-10-22 | Francis A. Karwacki |
| A superconducting Josephson junction gyroscope for detecting rotational motion of a vehicle about an axis. A persistent current of Cooper-paired electrons travels around a thin-film superconducting ring and the phase change across a Josephson junction in the ring produces an output signal directly proportional to the rate of rotation of the platform. | ||||||
| 75 | Gas rate sensor system | US295839 | 1989-01-11 | US5012676A | 1991-05-07 | Tsuneo Takahashi; Tomoyuki Nishio; Masayuki Ikegami; Takahiro Gunji |
| Disclosed is a gas rate sensor system which provides an output signal representing an angular velocity of the gas rate sensor when the gas flows more on one of its thermal sensing elements than on the other due to the effect of the angular velocity on the gas flow. The gas rate sensor system can carry out an arithmetic operation for correction of gas rate sensor output signal by selectively using a preset value representing the change of the gas rate sensor output signal with temperature in the gas rate sensor. | ||||||
| 76 | Gas rate sensor | US295838 | 1989-01-11 | US4951507A | 1990-08-28 | Tsuneo Takahashi; Tomoyuki Nishio; Masayuki Ikegami; Takahiro Gunji |
| Disclosed is a gas rate sensor system which provides an output signal representing an angular velocity of the gas rate sensor when the gas flows more on one of its thermal sensing elements than on the other due to the effect of the angular velocity on the gas flow. The gas rate sensor system can carry out an arithmetic operation for correction of gas rate sensor output signal by renewing and using an effect value to meet the instantaneous temperature change in the gas rate sensor. | ||||||
| 77 | Constant gain laminar jet angular rate sensing device | US281680 | 1988-12-09 | US4945764A | 1990-08-07 | Gary L. Frederick |
| A laminar jet angular rate sensor senses inertial angular rate in flight control and stabilization systems for aircraft and other vehicles. The sensor utilizes fluid as a power source and may be interfaced directly with fluid powered actuators for closed loop rate stabilization of the vehicle. To be practical, the rate sensor must exhibit consistent operation over the side range of supply fluid temperatures seen in a typical application. This invention involves apparatus for providing constant sensor gain over a wide range of fluid viscosity conditions. To achieve this, the pressure drop across the rate sensor is varied proportional to supply fluid viscosity to overcome viscous momentum losses in the jet and provide a constant gain characteristic. The specific apparatus of the invention utilizes a pressure regulator with a fluid viscosity sensor to accurately provide the required supply pressure proportional to fluid viscosity schedule. | ||||||
| 78 | Strapdown measuring unit for angular velocities | US231496 | 1988-08-12 | US4901565A | 1990-02-20 | Helmut Seidel; Fritz Hofmann |
| A strapdown measuring unit for measuring the angular velocities about the three axes of a flying body rotating relatively fast about its first axis is disclosed. The unit combines a Sagnac effect sensor for roll rate determination and two micro-mechanical acceleration sensors whose output, combined mathematically with the output of the Sagnac effect sensor, determines the angular velocity of the remaining two axes. The mathematical calculations are performed by a dedicated microprocessor which is integrated with the three sensors into a single small unit. | ||||||
| 79 | Method of manufacturing fluidic angular rate sensor | US198044 | 1988-05-24 | US4823461A | 1989-04-25 | Fumitaka Takahashi; Kunio Okazaki; Masaru Shiraishi; Masayuki Takahashi |
| A method of manufacturing a fluidic angular rate sensor of the type wherein fine wires, such as tungsten wires, are mounted in tension over the heads of two pairs of spaced apart metal supports which are mounted on a ceramic disc having fluid passage apertures therein, comprising plating gold on the wires; fixedly mounting the wires between the spread apart metal supports by means of thermocompression bonding or the like; and heating the mounted gold plated wires in a predetermined atmosphere for removing the plated gold from the wires and to recrystallize the wires. | ||||||
| 80 | Angular velocity sensor having low temperature sensitivity | US663525 | 1984-10-22 | US4726227A | 1988-02-23 | E. Marston Moffatt; Richard E. Swarts |
| An angular velocity sensor utilizing the Coriolis effect on a fluid jet employs a metal diaphragm impulse jet pump with no valves to reduce temperature sensitivity. The pump anvil, the nozzle block and the sensor plug may all be fabricated of the same material to further reduce temperature sensitivity. The thickness of the sensing elements is selected to reduce temperature sensitivity still further. | ||||||
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