Class / Patent application number | Description | Number of patent applications / Date published |
073147000 | WIND TUNNEL: AERODYNAMIC WING AND PROPELLER STUDY | 42 |
20080257029 | System for Setting a Spatial Position for a Motor Vehicle - A system for setting a spatial position of a vehicle relative to a foundation, on which the vehicle is standing with its wheels, in particular in a wind tunnel, is provided. The adjusting system includes a plurality of linear actuating devices, which are assigned to each one of the wheels and which are mounted on the vehicle in the area of the respective wheel and with which in the area of the respective wheel a distance between the foundation and a vehicle chassis can be set. The adjusting system includes a plurality of measuring devices, which are assigned to each one of the actuating devices, for determining the distance between the foundation and the vehicle chassis in the area of the respective wheel. | 10-23-2008 |
20090158835 | Vertical Wind Tunnel With Viewing Facility - The invention refers to a wind tunnel designed to operate in its vertical section that is to say, air currents generated by appropriate means meeting in a vertical area at the end of which the air current is capable of lifting objects in this vertical area. At the same time this lifting effect may be seen on the outside as it has been built from translucent materials. The viewing and lifting of bodies in this device allows both their display and measurements to be taken. | 06-25-2009 |
20090255330 | AERODYNAMIC HOOD LIFT AND DEFLECTION MEASUREMENT DEVICE - An aerodynamic hood lift deflection measurement device includes an airfoil body mounted to a front vehicle fender such that a portion of the airfoil body held over the vehicle hood. A laser measurement device is secured to the airfoil body in a position so as to be directly over the vehicle hood. The airfoil body is mounted at an angle such that a length direction of the airfoil body is parallel to an air flow direction. The resultant disruption of the air flow surrounding the vehicle hood is minimized due to the shape and positioning of the measurement device. | 10-15-2009 |
20090272184 | Minimum aerodynamic interference support for models in a cryogenic wind tunnel - Minimum aerodynamic interference support for models in a cryogenic wind tunnel comprising two main pieces: a front sting substantially parallel to the longitudinal axis of the model and a blade, integrated together and describing an obtuse angle. The support is connected to the model by means of the blade, being the model such that it emulates a tail section and/or wings of an aircraft. The front sting of the support comprises an extension, extended horizontally underneath a frontal zone of the fuselage of the model, starting from the point where the blade starts and up to surpassing the point where the blade is connected to the model, in such a way that the length and area dimensions of the cross-section of the extension are obtained by applying the aerodynamic principle, area rule, to the ensemble made up by the front sting, the blade, the model and the extension. | 11-05-2009 |
20090277263 | WIND TUNNEL - The invention relates to closed-circuit tunnels used for aerodynamic researches, sportsmen-parachutists training and other purposes. The inventive closed-circuit tunnel comprises a confuser, a working area, a diffuser, one or several return channels, a blower unit and turning bends having different flow deflection angle, wherein the bend having the smaller flow deflection angle is placed in a high-speed flow cross-section, whereas the bend having the greater flow deflection angle is arranged in a low flow speed cross-section. In a preferred embodiment, the tunnel comprises a first turning bend containing one turning gut for turning the airflow at 60 degrees, a second turning bend containing two turning guts for turning the airflow at 120 degrees, and a third turning bend containing three turning guts for turning the airflow at 180 degrees. The invention makes it possible to reduce air pressure losses, the drive power and a specific amount of metal per structure. | 11-12-2009 |
20090314076 | HYBRID METHOD FOR ESTIMATING THE GROUND EFFECT ON AN AIRCRAFT - A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft. | 12-24-2009 |
20090320582 | Wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, as well as method - A wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, wherein the wind tunnel comprises at least one computer unit and at least one visual display terminal particularly at least one monitor, as well as at least one sensor for acquiring the measuring data. A plurality of measuring data of the wind tunnel, particularly measuring data on flow and/or pressure conditions on the model and/or in the region of the model, which data are determinable by the at least one sensor, can be processed in real time and with consideration of geometrical data of the model by the at least one computer unit and visualized on the at least one visual display terminal during a wind tunnel measurement. | 12-31-2009 |
20100064793 | DEVICE FOR AUTOMATIC EVALUATION AND CONTROL OF WIND TUNNEL MEASUREMENTS - A device for evaluating a wind tunnel measurement, in which a processor identifies a flow element on an image recorded in the wind tunnel. The identified flow element subsequently may be segmented and further analyzed in order to obtain accurate information about the flow behaviour of an object to be analyzed. In addition, a method, a computer-readable storage medium, a program element, and an arrangement are disclosed. | 03-18-2010 |
20100071455 | METHOD AND MEASURING DEVICE FOR MEASURING OVERLAP ON AN AIRCRAFT WING - The present invention relates to a method and a measuring device for measuring and displaying the overlap between a rear edge of an aircraft wing and a front edge of a landing flap fixed thereto. In accordance with the invention, only the difference in the positions of the rear edge of the aircraft wing and the front edge of the landing flap relative to the longitudinal direction of the aircraft is determined. For this purpose, a first sensor is positioned, as a reference of sorts, at one of the two positions, for example at the rear edge of the aircraft wing, and the display is then reset to zero or to another reference value. By positioning the second sensor, which is also rigidly connected to the calliper, at the other respective position, for example at the front edge of the landing flap, the difference between the front edge of the landing flap relative to the rear edge of the aircraft wing is established. This value, which directly indicates the overlap value, can now be read directly from the display of the calliper. | 03-25-2010 |
20100116044 | METHOD AND SYSTEM FOR TURBINE BLADE CHARACTERIZATION - Methods and systems providing for characterizing turbine blades, including characterizing the dynamics of one or more turbine blades or stages of a stage in terms of natural frequencies, normalized response intensity, and/or stage modal shape or nodal configuration. Such methods and systems comprise fluid (e.g., oil) excitation of bladed disks and quantitative modeling of the fluid excitation. Additionally or alternatively, such methods and systems may provide for analyzing modal shape or nodal configuration of a bladed disk (e.g., a turbine stage) based on a phase analysis of strain signals acquired from a bladed disk subjected to a fluid excitation, wherein the modal shape or nodal configuration corresponds to modes of blades coupled through a disc or shrouding. | 05-13-2010 |
20100132446 | WIND TUNNEL TESTING TECHNIQUE - A wind tunnel testing technique or method involves using feedback to position control surfaces of a model so that there is substantially no moment on the model for its given orientation to the airstream. The model is mounted on a sting that allows change in orientation of the model relative to the airstream. A balance is used to provide data regarding the forces and/or moments on the model. This data on forces and/or moments is used in one or more feedback loops to position the control surfaces of the model so that there are substantially no moments on the model. This may be done automatically, with a controller automatically controlling the position of the control surfaces to zero out the moments on the model. The use of the method may allow faster determination of model characteristics, such as determination of the trim envelope of the model. | 06-03-2010 |
20100139384 | CURRENT TANK SYSTEMS AND METHODS - There is disclosed a current tank system comprising a first current tank adapted to produce a first current in a first direction, and a second current tank adapted to produce a second current in a second direction. There is also disclosed a method of testing a sample, comprising exposing the sample to a first current in a first current tank, and exposing the sample to a second current in a second current tank. | 06-10-2010 |
20100154528 | Aerodynamic Measurement Probe and Helicopter Equipped with the Probe - The invention relates to a probe for aerodynamic measurement of an airflow. The probe comprises a plate rotating about an axis, a transmitter for transmitting a sound wave and a receiver responsive to the sound wave, the transmitter and the receiver forming two elements which are integrally connected to the plate and are placed at separate positions on the plate, the probe furthermore comprising means for delivering information representing a time of flight of the sound wave between the two elements and a temporal variation of the information. In the case of using the probe on board a helicopter, the rotating plate is advantageously placed at the centre of the rotor of the helicopter while being integrally connected to it. This type of probe makes it possible to carry out aerodynamic measurements even at low airspeeds of the helicopter. | 06-24-2010 |
20100170333 | FLUID FLOW MONITORING - In order to discriminate between laminar flow and turbulent flow states, and to provide an indication, e.g. to a pilot of an aircraft of air flow over an aircraft wing, a sensor mounted on the wing provides an analogue signal of airflow, and an intermittency value of the analogue signal is derived in analogue circuitry including an AC coupling of the signal to an integrator for integrating the signal for a preset time. The integrated value is compared with a threshold value to indicate whether the intermittency represents quiet laminar flow or noisy turbulent flow. | 07-08-2010 |
20100170334 | SYSTEM FOR SIMULATING THE GROUND EFFECT FOR TESTING VEHICLES OR THEIR SIMULACRA IN WIND TUNNELS - A system for simulating the ground effect for testing vehicles or their simulacra in wind tunnels includes a resting surface for the vehicle incorporating a moving belt for simulation of the ground, extending between the wheels of the vehicle, at least from one end to the other of the vehicle, as well as two auxiliary moving belts set immediately adjacent to the two sides of the front portion of the main moving belt, for simulating the ground in areas in front of the front wheels of the vehicle. | 07-08-2010 |
20100175465 | TEST SECTION FOR WIND-TUNNEL TESTING APPARATUS AND WIND TUNNEL TEST APPARATUS EMPLOYING THE SAME - Provided is a test section for a wind-tunnel testing apparatus that is capable of suppressing the influences of a boundary layer on the floor surface and incoming airflows from the sides, and that is capable of measuring aerodynamic forces closer to the those actually occurring. A test section for a wind-tunnel testing apparatus having a mounting section that mounts an automobile along the internal floor surface of a wind tunnel, tests being conducted by applying an airflow blown in the wind tunnel to the automobile mounted on the mounting section, includes a slit that is disposed on the floor surface located on the upstream side of the mounting section with respect to the airflow direction so as to extend in the intersecting direction intersecting the airflow direction and that sucks in a portion of the airflow near the floor surface; and lateral suction portions, disposed at both sides of the mounting section, that suck in the incoming airflows R flowing in from the sides of the mounting section. | 07-15-2010 |
20110100109 | Compact Wind Tunnel Instrument - Provided is a compact wind tunnel instrument. The compact wind tunnel instrument includes a blowing unit configured by a plurality of blowing devices provided in the same plane, and a control unit for controlling them, thereby easily providing a variety of wind environments. | 05-05-2011 |
20110107829 | RESONANT FLOW SENSOR AND USES AND PRODUCTION METHODS FOR THE SAME - The invention relates to a flow state sensor ( | 05-12-2011 |
20110138900 | Weatherized direct-mount absolute pressure sensor - A piezoresistive sensor assembly is provided that has a flex circuit having at least one air flow aperture formed therein. A sensor die is coupled to an absolute support and the flex circuit. The sensor die has a diaphragm that deflects in response to air flow that flows through the air flow aperture and is incident on the diaphragm. The sensor die includes one or more gages positioned on or in the diaphragm. | 06-16-2011 |
20110138901 | METHOD OF WIND TUNNEL MEASUREMENT OF AIRFOIL - A method of wind tunnel measurement of airfoil, includes a step of providing a wind tunnel test apparatus. The wind tunnel test apparatus includes two walls, two supporting members, and two load measuring units. The method further includes steps of: coupling both ends of an airfoil model under test with the two supporting members, respectively; generating a flow of a fluid in the wind tunnel flow path; and measuring a load applied to the airfoil model by using the two load measuring units. A thin film member is stuck on each end of the airfoil model so that a part of the thin film member protrudes from the each end of the airfoil model along an outer circumference throughout an entire circumference. The thin film member has a strength at which the thin film member enables to endure a pressure of the fluid, and is formed of a material which is elastically deformable. The thin film member is provided so that a gap between the each end of the airfoil model and one of the two walls facing to the each end of the airfoil model is blocked. | 06-16-2011 |
20110138902 | MEMS MICROPHONE ARRAY ON A CHIP - The present invention relates to microelectromechanical systems (MEMS). In particular, the present invention relates to MEMS arrays for use in acoustics and other applications. | 06-16-2011 |
20110185803 | BICYCLE FITTING APPARATUS AND METHOD - A bicycle fitting system includes a wind tunnel, a platform, a load cell, a bicycle rig, a plurality of actuators, and a processor. The platform is disposed within the wind tunnel and includes a rear roller, a front strut, and a rear strut. The load cell is coupled to the platform. The bicycle rig is coupled to the front and rear struts and includes a plurality of adjustment points, a rear wheel, a handle bar, and a seat, with the rear wheel friction coupled to the rear roller. Each adjustment point is associated with one of the actuators, and each actuator is operable to alter a configuration of the bicycle rig. The processor receives an output from the load cell and operates the actuators while a rider is riding the bicycle rig. | 08-04-2011 |
20120125091 | Aerodynamic Testing Method and Apparatus - An aerodynamic testing apparatus includes a test object carrier that carries a test object along an orbital test path through a fluid test medium. The apparatus may be configured to carry a test object along a generally spiraling orbital test path through the fluid test medium. | 05-24-2012 |
20120144911 | WIND TUNNEL FOR STUDYING VAPORIZATION OF LIQUIDS - A wind tunnel making it possible to measure the vaporization parameters of a test liquid exposed in a gas flow is disclosed. The wind tunnel comprises: a gas generator configured to generate a gas at a flow rate and at a temperature that are adjustable; a conditioning device designed to obtain a horizontal and uniform flow of the generated gas; a measurement chamber containing the liquid to be tested and various measurement devices making it possible to characterize the flow of gas passing through the measurement chamber; a tapping and analysis zone in which the gas-and-vapor mixture is tapped analyzed; and a discharge zone configured to discharge the gas-and-vapor mixture. The liquid to be tested in the tunnel presents a free surface positioned inside the measurement chamber in a manner such that it is swept continuously and tangentially by the uniform flow of gas. | 06-14-2012 |
20120167675 | WIND TUNNEL WITH A CLOSED SECTION FOR AEROACOUSTIC MEASUREMENTS WITH AN ANECHOIC COATING - A wind tunnel with a closed section for aeroacoustic measurements with an anechoic coating including: a) a first cavity having a thickness D | 07-05-2012 |
20120255350 | APPARATUSES AND METHODS FOR VISUALIZING AIR FLOW AROUND VEHICLES - Described herein are embodiments of an apparatus for visualizing air flow around a vehicle. Such embodiments can comprise one or more gas emitters supportable by a vehicle, one or more imaging devices having a field of view of at least a portion of the gas flowing over the vehicle, and a light source for irradiating at least a portion of the field of view of the one or more imaging devices. Some embodiments of the apparatus can have a signal processor configured to generate an image based on an input from the imager. The apparatus can be configured such that the gas is not detectable to the naked eye so as to not obstruct a vehicle operator's field of vision. The apparatus can be configured to produce an image of the flow of the gas over the one or more surfaces of the vehicle when in an operational state. | 10-11-2012 |
20130145836 | Probe for Measuring a Local Angle of Attack and Method Implementing Same - A probe for measuring a local angle of attack designed to be fixed to a wall and a method implementing the probe are provided. The probe comprises at least three pressure sampling ports disposed over a nose of the probe body, pressure measurement means associated with the pressure sampling ports and calculation means capable of determining an angle of attack of the flow with respect to the main direction of the probe body as a function of the pressures measured by the pressure measurement means. The calculation means are configured for choosing from amongst the pressure sampling ports those allowing the best measurement precision of the local angle of attack to be obtained and for calculating the local angle of attack with respect to the main direction using the pressure measurements carried out in the chosen pressure sampling ports. | 06-13-2013 |
20130180325 | NOVEL LOW SPEED WIND TUNNEL DESIGN FOR AGRICULTURAL SPRAY PARTICLE ANALYSIS - A wind tunnel device defines a cyclical tunnel to receive continuous airflow. Airflow is delivered through the tunnel to a testing region that includes a first portion carrying an arm including a spray tip configured to spray particulates in the testing region at an angle, and a second portion including an enlarged cutout region configured to receive the angled sprayed particulates. As airflow carries the angled spray particulates into the second portion, the enlarged cutout region enables the spray particulates to pass through and exit the second portion of the testing region. Analysis in the second region may be conducted through transparent walls free of openings to minimize exposure of the spray particulates to the exterior of the device. A scrubber is adapted to extract spray mist from the airflow as the airflow exits the testing region and is re-circulated through the cyclical tunnel. | 07-18-2013 |
20130298659 | Wind Tunnel Model Measuring System and Method - There is provided a wind tunnel model measuring system for use with a wind tunnel. The system has a measuring assembly with an automated movable structure with at least one measuring device mounted thereon and configured for placement within the wind tunnel, and a measuring controller device located outside the wind tunnel to control the automated movable structure in order to remotely move the automated movable structure from a storage position within the wind tunnel to one or more operating positions with respect to a wind tunnel model within the wind tunnel and to allow the at least one measuring device to determine a relative position of at least one movable first component with respect to a second component, both of the wind tunnel model. The system further has a processing device configured for placement outside the wind tunnel and coupled to the measuring controller device. | 11-14-2013 |
20140069182 | TESTING APPARATUS AND METHOD - An apparatus for testing effects of relative movement of a fluid and an object has a test chamber ( | 03-13-2014 |
20140076041 | Correction of Pressure Signals Measured During Supersonic Wind Tunnel Testing - A method for removing interference-induced distortion effects from an environment used to experimentally measure aerodynamic signatures. A space marching algorithm is used to extract the effects of environment including rail and wall reflections and rail edge effects to create an interference-free pressure signature. | 03-20-2014 |
20140182367 | LOW SPEED WIND TUNNEL DESIGN FOR AGRICULTURAL SPRAY PARTICLE ANALYSIS - A wind tunnel device defines a cyclical tunnel to receive continuous airflow. Airflow is delivered through the tunnel to a testing region that includes a first portion carrying an arm including a spray tip configured to spray particulates in the testing region at an angle, and a second portion including an enlarged cutout region configured to receive the angled sprayed particulates. As airflow carries the angled spray particulates into the second portion, the enlarged cutout region enables the spray particulates to pass through and exit the second portion of the testing region. Analysis in the second region may be conducted through transparent walls free of openings to minimize exposure of the spray particulates to the exterior of the device. A scrubber is adapted to extract spray mist from the airflow as the airflow exits the testing region and is re-circulated through the cyclical tunnel. | 07-03-2014 |
20140208839 | OPEN AREA PLATFORM FOR WIND TUNNEL TESTING - An open area platform for supplementing operation of a wind tunnel balance, comprises a platform body and platform adapters. The platform adapter members have first ends and second ends. The first ends are configured to contact the platform body and the second ends are designed to be operatively coupled with the wind tunnel's balance. As a result, any load on the platform body is configured to be transmitted through the platform adapter members and measured by the wind tunnel balance. Methods of using the open area platform, including for the testing of athletes and their equipment, are also disclosed. | 07-31-2014 |
20140373615 | MODEL MOTION SYSTEM FOR A VEHICLE MODEL - A model motion system for providing controlled motion of a vehicle model with wheels on is provided. The model motion system includes a pitch system coupled to the vehicle model with wheels on to control a pitch range of motion of the vehicle; a roll system coupled to the vehicle model with wheels on to control a roll range of motion of the vehicle; and a yaw system coupled to the vehicle model with wheels on to control a yaw range of motion of the vehicle. The pitch system, the roll system, and the yaw system control the respective ranges of motion of the vehicle model with wheels on. | 12-25-2014 |
20150013445 | WIND TUNNEL BALANCE AND SYSTEM WITH WING MODEL AND WIND TUNNEL BALANCE - A wind tunnel balance, with a tunnel wall adaptor configured to fasten the wind tunnel balance to a wall of a wind tunnel, an actuator housing connected to the tunnel wall adaptor, a plurality of force sensors arranged between the actuator housing and the tunnel wall adaptor and which are configured to detect forces acting on the actuator housing, a pivot coupling, by means of which an airfoil model of an aircraft can be pivotably coupled to the actuator housing, and a plurality of piezoelectric actuators arranged in the actuator housing and which are configured to controllably deflect an airfoil model mounted on the pivot coupling in three spatial directions. | 01-15-2015 |
20150020586 | APPARATUS FOR LOCATION OF VEHICLE CENTER FOR AERODYNAMIC TESTING - In accordance with one aspect of the present disclosure, an apparatus and a method of testing one of aerodynamic and acoustic characteristics of a vehicle is described. The method includes measuring a vehicle center using a gauge. The gauge includes a carrier section from which a pair of arms extend in opposed directions. Each of the arms has an axle center locator. The carrier section has a vehicle center marker. Upon determination of the vehicle center, the vehicle can be located in a wind tunnel at a predetermined location and exposed to an enhanced air flow. | 01-22-2015 |
20150307202 | Boundary Layer Flow Sensor - Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use. | 10-29-2015 |
20150308922 | MORPHING CERAMIC COMPOSITE COMPONENTS FOR HYPERSONIC WIND TUNNEL - In one embodiment, a morphable composite three-dimensional structure is disclosed. The morphable composite three-dimensional structure comprises a flexible fiber-reinforced ceramic composite comprising a fiber preform and a ceramic matrix material infused therein. The flexible fiber-reinforced ceramic composite defines a flowpath having a three-dimensional cross-section. The cross-section of the flowpath is variable along the length of the flowpath. A plurality of anchors are integrally formed in the fiber preform. The plurality of anchors extend through a thickness of the ceramic matrix. The plurality of anchors are configured to couple to at least one actuator. The at least one actuator is actuatable to vary the three-dimensional cross-section of the flowpath. | 10-29-2015 |
20150346051 | MEASUREMENT of VEHICLE DRAG in a WIND TUNNEL - A method and apparatus for measuring the propulsive power required to overcome drag forces on a vehicle mounted within a wind tunnel. The apparatus includes a running belt platform driven by a dynamometer and supporting the vehicle placed inside a wind tunnel and controlled by a closed-loop servo control system, which maintains the vehicle centered on the running belt under varying operating speeds and headwind conditions. | 12-03-2015 |
20150346052 | LOW SPEED WIND TUNNEL DESIGN FOR AGRICULTURAL SPRAY PARTICLE ANALYSIS - A wind tunnel device defines a cyclical tunnel to receive continuous airflow. Airflow is delivered through the tunnel to a testing region that includes a first portion carrying an arm including a spray tip configured to spray particulates in the testing region at an angle, and a second portion including an enlarged cutout region configured to receive the angled sprayed particulates. As airflow carries the angled spray particulates into the second portion, the enlarged cutout region enables the spray particulates to pass through and exit the second portion of the testing region. Analysis in the second region may be conducted through transparent walls free of openings to minimize exposure of the spray particulates to the exterior of the device. A scrubber is adapted to extract spray mist from the airflow as the airflow exits the testing region and is re-circulated through the cyclical tunnel. | 12-03-2015 |
20150346078 | APPARATUS AND METHOD FOR ASSISTING WITH FLUID PRESSURE MEASUREMENT - An apparatus for assisting with measurement of a fluid pressure includes a cover layer having a leading cover edge and upper and lower cover surfaces. A cover aperture fluidly connects the upper and lower cover surfaces. A spacer layer has oppositely facing upper and lower spacer surfaces. A cavity has an upper cavity surface, defined by the lower cover surface, which includes the leading cover edge and the cover aperture. A measuring tube is located adjacent to the upper cover surface. The measuring tube includes a tube lumen. When the lower spacer surface is connected to the substrate, the substrate defines a lower cavity surface and extant fluid is present within the cavity. Variable fluid flowing toward the cavity exerts pressure on the extant fluid to generate an extant fluid pressure level which is physically transmitted through the apparatus and made available for measurement as an extant fluid pressure level. | 12-03-2015 |
20170234764 | Wind tunnel for human flight | 08-17-2017 |