235 results about "Vertical velocity" patented technology

A control system for a resilient support mechanism such as a suspension mechanism of a wheeled vehicle including a damper disposed between an unsprung mass member and a sprung mass member of the vehicle, wherein a damping coefficient of the damper is divided into a linear portion and a nonlinear portion, and wherein the nonlinear portion of the damping coefficient is defined as a control input u and applied with a frequency weight Wu(s), while a vertical velocity of the sprung mass member, a relative velocity of the sprung mass member to the unsprung mass member and a vertical acceleration of the sprung mass member are defined as an evaluation output zp and applied with a frequency weight Ws(s). In the control system, a nonlinear Hinfin control theory is applied to a generalized plant to obtain a positive definite symmetric solution P and to calculate a target damping force based on the positive definite symmetric solution P and a state amount such as the vertical velocity of the sprung mass member, a relative displacement of the sprung mass member to the unsprung mass member or the like.

The instant invention provides a method for processing converted-wave data into interpretable images using a compact two-parameter model. The method broadly comprises the steps of: collecting both P-wave and converted-wave seismic data; identifying the arrival times of the P-wave and the converted-wave data; computing the vertical velocity ratio from the arrival time data; computing the moveout velocity ratio from the corresponding moveout velocities; computing the effective velocity ratio from the vertical velocity ratio and the moveout velocity ratio; and computing the conversion point from the short-spread P-wave moveout velocity for each reflector, from the effective velocity ratio, the C-wave moveout velocity ratio, and from the arrival time data.

A seed delivery system for use in a seeding or planting machine that removes the seed from a seed meter by capturing the seed therefrom. The delivery system then moves the seed down to a lower discharge point and accelerates the seed horizontally rearward to a speed approximately equal to the forward travel speed of the seeding machine such that the seed, when discharged has a low or zero horizontal velocity relative to the ground. Rolling of the seed in the trench is thus reduced. Furthermore, as the seed only has a short drop from the outlet to the bottom of the seed trench, the seed has little vertical speed to induce bounce. The delivery system uses a brush belt to capture, move and accelerate the seed. By capturing the seed and moving it from the meter to the discharge, the seed is held in place relative to other seeds and the planter row unit. As a result, the seeds are isolated from row unit dynamics thereby maintaining seed spacing.

The field of invention is computer-implemented methods and systems for distributing targeted messages and the serving, collecting, managing, and analyzing and reporting of information relating to mobile and other electronic devices. Targeting of messages can be improved by employing additional variables to target messages. In the push message process (1000) a message is sent to users of mobile devices based on one or more variables that may include current location as well as temporal variables such as time of day and other spatial or kinetic variables—measured and / or derived—including but not limited horizontal velocity, vertical velocity, heading, orientation, travel distance, travel time, range and / or past points of reference in additional variables such as demographics, user preferences, and / or purchasing behavior. The user may be prompted to take an action in response to the message. In the user request process (2000) a user may make a request for information with or without first receiving a message. The request may be based on one or more variables that may include current location and geographic variables such as altitude as well as temporal variables such as time of day and other spatial or kinetic variables. Information is collected, managed, analyzed, and reported in the collect information process (3000), manage information process (4000), and analysis and report information process (5000), respectively. In addition, such methods and systems can also be used for advertising, marketing, promotions, campaigns, orders, sales, subscriptions, donations, pledges and so on.

A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts experienced while aircraft are executing either normal or hard landing events. A high speed computer attached to high speed cameras, or range-finders, mounted in relation to each of the landing gear struts are used to monitor, measure and record the landing gear compression rates and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. The system also determines through landing gear strut compression rates if aircraft landing limitations have been exceeded.

In a vehicular control device, it is necessary to measure or calculate six physical quantities-forward-reverse speed, left-right speed, vertical speed, pitch angle, roll angle, and angle of sideslip-representing vehicular movement and to control the braking force of each wheel and / or the damping coefficient of each suspension shock absorber in order to further shorten braking distance particularly at the time of braking and to prevent spin at that time. In this case, it is necessary to furnish sensors to measure speed and angle directly. In the present invention, four radar sensors are used in order to directly measure the forward-reverse speed and the left-right speed. Also, the vertical speed, the pitch angle, the roll angle, and the angle of sideslip are indirectly measured from the output of the radar sensors. By using three or four radar sensors, six physical quantities-the forward speed, the left-right direction speed, the vertical speed, the angle of sideslip, the pitch angle, and the roll angle-can be measured. Also, by using two radar sensors, three physical quantities-the forward speed, the left-right speed, and the angle of sideslip-can be measured.

A flight control system includes a collective position command algorithm for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command algorithm utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

A system for use in monitoring, measuring, computing and displaying the Kinetic Energy generated and experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.

The invention belongs to the field of small unmanned gyroplane autonomous flight control research, provides a multi-sensor information fusion-based method for measuring the height of a small unmanned gyroplane, and aims at providing real-time, precise and reliable height information for the small unmanned gyroplane. The adopted technical scheme is as follows: a sonar arranged at the bottom of the unmanned gyroplane is used for acquiring the distance from the sonar to the ground, and the distance is used as a sonar measurement height; an accelerometer is utilized for acquiring the triaxial accelerated speed of the unmanned gyroplane under an object coordinate system, thereby acquiring the vertical acceleration in a geodetic reference system; a barometer is used for measuring barometric pressure information of the unmanned gyroplane at certain height, comparing the barometric pressure information of the unmanned gyroplane at certain height with ground barometric pressure information, substituting a comparing result into a standard atmosphere model to obtain the height measurement information based on the barometric pressure measurement; and the multi-sensor information fusion height measurement method is adopted for obtaining the high-frequency real-time height and vertical velocity information by use of the inputs. The method is mainly applied to the unmanned gyroplane autonomous flight control.

The invention relates to a self-evolution ANFIS and UKF combined GPS / MEMS-INS integrated positioning error dynamic forecasting method. The method comprises the following steps of: (1) off-line confirming an ANFIS structure and an initial premise parameter according to a mass of experimental data comprising different motion characteristics of a carrier; (2) performing the self-evolution real-time updating of an ANFIS model by using an east, north and vertical velocity and GPS signal loss time outputted by the corresponding MEMS-INS under a UKF forecasting mode as input of the ANFIS and using an error value of a position error outputted under two modes of the UKF is used as expected output of the ANFIS, wherein the UKF comprises two concurrent working modes, namely, a forecasting mode and an updating mode, when a GPS / MEMS-INS integrated navigation system starts to work and the GPS signal is in good condition; and (3) forecasting the position error and correcting by a method of dynamically combining the ANFIS mode prediction with the UKF prediction when the GPS signal is lost and the ANFIS mode and the UKF work in a forecasting mode, and outputting the corrected integrated navigation system result. The method enhances the dynamic property and the adaptive ability of the ANFIS mode, and improves the position performance of the integrated navigation system.

A legged robot that runs while repeating a jump cycle including a ground-contact phase from a landing to a takeoff and an aerial phase from a takeoff to a landing is provided. The legged robot adjusts the landing timing after a jump in accordance with a planned timing, thereby attaining a smooth landing. A measuring unit of the legged robot measures an actual aerial phase period in a k-th jump cycle. A subtractor calculates a time difference between a target aerial phase period and the actual aerial phase period in the k-th jump cycle. A target velocity determining unit calculates a target vertical velocity of a center of gravity on a takeoff timing in a (k+1)-th jump cycle so as to eliminate the time difference. Motors in respective joints are controlled so as to realize the calculated target vertical velocity in the (k+1)-th jump cycle. As a result, the time difference generated in the k-th jump cycle in the (k+1)-th jump cycle can be compensated, thereby adjusting the landing timing with the planned landing timing, resulting in the jump motion with smooth landing.

A system and method of generating a landing trajectory for use in landing an aircraft onto a deck of a waterborne ship includes sensing motion of the ship, and sensing wind speed and wind direction. The sensed motion of the ship is processed to generate estimates of ship attitude and vertical speed, and the sensed wind speed and wind direction are processed to generate estimates of air-wake disturbances ahead of the aircraft. The landing trajectory is generated based on the estimates of ship attitude and vertical speed and the estimates of air-wake disturbances. The system and method implement model predictive control to calculate the control maneuvers multiple steps ahead, which provides the capability to smoothly control the timing of the aircraft touchdown phase.

An electronically-controlled suspension apparatus includes a first sensing device for detecting a vertical acceleration of a vehicle body; a second sensing device for detecting vertical movements of a vehicle body relative to a wheel axle; and a controller for obtaining a vertical speed of the vehicle body by using the vertical acceleration detected by the first sensing device, obtaining a damper speed of a variable damper by using the vertical movements detected by the second sensing device, calculating a target damping force by using the vertical speed of the vehicle body and the damper speed, and determining a control command value by using the target damping force. The control command value is transmitted from the controller to the actuator of the variable damper to change damping force characteristics of the variable damper.

An apparatus 10 for measuring and / or analyzing the rollover characteristics of a vehicle 12. Apparatus 10 includes a controller 14, a selectively movable test fixture assembly 16, a truck or towing vehicle 18 which is coupled to trailer assembly 16 and which selectively tows or drives assembly 16, several cameras 22, 24, 26 and 28, and a user interface 30. Vehicle 12 is attached to test fixture 16, and user interface 30 is used to activate motor assembly 36 which selectively rotates vehicle 12 to a desired roll angle 90 relative to the ground surface 43. Once vehicle 12 is correctly positioned, an operator drives truck 18 at a predetermined and desired speed. Controller 14 generates release signals to exploding bolts 86, 88, which simultaneously explode, thereby releasing vehicle 12 from frame 32. In this manner, apparatus 10 allows the drop height and the translational and vertical velocity of a vehicle to be selectively controlled, adjusted and repeated from test to test, and provides controllable and predictable roof-to-ground impacts.

A method for estimating seismic velocities in vertically transversely isotropic media includes generating an initial estimate of vertical interval velocity and interval normal moveout velocity with respect to depth from seismic data. An initial estimate is generated of a first anisotropy parameter with respect to depth. The first anisotropy parameter is related to the interval normal moveout velocity and the interval vertical velocity. An initial estimate is generated with respect to depth of a second anisotropy parameter. The second anisotropy parameter is related to the first anisotropy parameter and an interval anelliptic parameter. A first tomographic inversion is performed with respect to the interval normal moveout velocity and the second anisotropy parameter at a constant value of the first anisotropy parameter until travel time differentials reach minimum values. Layer depths are adjusted with the initial estimate of vertical interval velocity. Using values of the second anisotropy parameter determined in the first tomographic inversion, a second tomographic inversion is performed of interval normal moveout velocity and the first anisotropy parameter with respect to depth. The adjusted layer depths, interval normal moveout velocities and interval vertical velocities are again adjusted and interval anelliptic parameters are calculated from the second tomographic inversion.

A flight control system and method for controlling the vertical flight path of an aircraft, the flight control system includes a stable decoupled model having a decoupled lateral equation of motion and a decoupled longitudinal equation of motion and a feedback command loop operably associated with the stable decoupled model. The feedback command loop includes a vertical flight path angle control law; an altitude control law; and a vertical speed control law.

The invention discloses a NRIET X-band radar cooperative networking analysis method. The method comprises the steps that data are collected; the data quality is controlled; a distance weight interpolation technology is used, and a three-dimensional cressman interpolation method is used to perform lattice interpolation on radar echo, radial wind and each polarization; three-dimensional data networking is carried out; for a three-dimensional wind field inversed by a dual Doppler radar, the inversed wind field is constrained by a mass continuous equation, and the three-dimensional wind field is acquired by repeatedly iteratively solving the equation; the vertical velocity w is acquired by the mass continuous equation, and a trace boundary condition is used to adjust a vertical motion field, wherein the upper boundary of the mass continuous equation is set to integrate down; based on a radar product reflectivity algorithm, a combined reflectivity puzzle product and an echo top puzzle product are generated; through Z-R relationship, quantitative precipitation is estimated to acquire a rain intensity product; a texture classification method is used to identify a precipitation stratus convection region; and a fuzzy logic algorithm is used to recognize the phase state of precipitation particles in each region at different stages of a precipitation process.

This invention provides a vehicle path grade angle measuring system and its measuring method. The measuring system includes: GPS speed measuring instrument, which is used to measure the flashy vertical velocity Vv and horizontal velocity Vh of the vehicles; the front suspension position sensing device installed at the front suspension of the vehicle, which is used to measure the related flashy displacement Zf of the body at the front suspension that is perpendicular to the path; the back suspension position sensing installed at the back suspension, which is used to measure the related flashy displacement Zf of the body at the back suspension that is perpendicular to the path; the electric control cell, which connects with the CPS speed measuring instrument, the front suspension position sensing device and the back suspension position sensing device to obtain the value of VvíóVhíóZfíóZr, and it computes the path grade angel ª’ according to the formula (1)íó(2) and (3). ª‡GPSú¢arctan(Vv / Vh) (1)ú” ª†ú¢arctan((Zf-Zr) / L) (2)ú” ª’ú¢ª‡GPS-ª† (3).

The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift / drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

A system for use in monitoring, measuring, computing and displaying the initial touch-down descent velocity experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.

Method for using the full wavefield (primaries, internal multiples and free-surface multiples) in inversion of marine seismic data, including both pressure and vertical velocity data (21), to infer a subsurface model of acoustic velocity or other physical property. The marine seismic data are separated (22) into up-going (23) and down-going (24) wavefields, and both wavefields are inverted in a joint manner, in which the final model is impacted by both wavefields. This may be achieved by inverting both wavefields simultaneously (25), or one after the other, i.e. in a cascaded approach (35→37, or 45→47), for the subsurface properties (26, 38, 48).

A walkaway VSP survey is carried out using a receiver array. First arrivals to a plurality of receivers are picked and used to estimate a normal-moveout (NMO) velocity. Using the NMO velocity and vertical velocities estimated from the VSP data, two anisotropy parameters are estimated for each of the layers. The anisotropy parameters may then be used to process surface seismic data to give a stacked image in true depth and for the interpretation purposes. For multi-azimuthal walkaway or 3D VSP data, we determine two VTI parameters ε and δ for multi-azimuth vertical planes. Then we determine five anisotropic interval parameters that describe P-wave kinematics for orthorhombic layers. These orthorhombic parameters may then be used to process surface seismic data to give a stacked image in true depth and for the interpretation purposes.

The invention provides a converted wave anisotropy velocity analysis method and device. The method includes the steps that the vertical velocity ratio, the effective velocity ratio and equivalent anisotropy parameters of converted waves are worked out according to the stacked section of longitudinal waves, the stacked section of the converted waves, the velocity of the longitudinal waves, the velocity of the converted waves and anisotropy parameters of the converted waves; with the speed of the converted waves, the vertical velocity ratio, the effective velocity ratio and the equivalent anisotropy parameters of the converted waves which are obtained as the initial parameters of pre-stack time migration of seismic data of the converted waves, the velocity parameter of pre-stack time migration of the converted waves is worked out, the first time of pre-stack time migration is performed, and a common imaging point gather is acquired; by analyzing the velocity of the converted waves corrected by residual moveout and the anisotropy parameters of the converted waves in the common imaging point gather, the common imaging point gather is acquired, and the velocity of the converted waves and the anisotropy parameters of the converted waves continue to be corrected till the acquired common imaging point gather is in even alignment in window. Through the converted wave anisotropy velocity analysis method and device, the accuracy of the converted wave anisotropy velocity analysis result is improved, and the processing cost is reduced.

The invention discloses a water surface aircraft water load full-aircraft power-free model pool test method. A test includes the following steps that firstly, full-aircraft power-free model test installation is performed; secondly, a full-aircraft power-free model pool test is performed, an electric cylinder (2) is started, an electromagnetic throwing device (3) is turned on, a full-aircraft power-free model (9) is thrown on the water surface at a constant vertical speed, the trailer speed, the water touching angle of the model, the overload and the pressure value are recorded at the same time, the water touching conditions of the model are recorded, and the loaded conditions of the model after the model touches the water are analyzed according to the model postures, the overloads and the pressure values of different test states. The water surface aircraft water load full-aircraft power-free model pool test method has the advantages of being practical, feasible, easy to operate, reliable in test result and wide in application range.

A system and method are described herein for detecting a user's transition between sitting and standing postures. Transitions between sitting and standing states are reliably detected using an accelerometer attached to the user. By modeling error introduced by the accelerometer, and correcting for this error, transitions between sitting and standing states are reliably detected. A microprocessor coupled to the accelerometer converts the captured accelerometer data to approximate vertical acceleration. Vertical velocity, which includes accelerometer error, is determined from the approximate vertical acceleration. The vertical velocity is corrected, and the corrected vertical velocity used to determine vertical displacement. Transitions between sitting and standing states are determined from the vertical displacement.

There is provided a fall detector for detecting falls of a user or an object to which the fall detector is attached, characterized in that the fall detector comprises an air flow sensor for providing measurements indicative of vertical velocity and / or changes in altitude of the fall detector.