128results about "Aircraft tyres" patented technology

A disclosed leaky coaxial resonant sensor system and methods. In use, the system includes at least one split-ring resonator (SRR) embedded within a material of the component. The at least one SRR is formed from a composite material. Additionally, the at least one SRR is configured to resonate at a first frequency in response to an interrogation signal from a leaky coaxial cable antenna. In some aspects, each SRR may resonate at a first frequency in response to an electromagnetic ping when the composite material is in a first state, and may resonate at a second frequency in response to the electromagnetic ping when the composite material is in a second state. A resonant frequency of the composite material may be based on physical characteristics of the composite material.

A method of copying data from a first device to a second device, each device including a wireless communication interfaces having a maximum range, is disclosed. The first device and the second device are separated by a distance greater than the maximum range. The method includes: transmitting, by the first device, the data to a third device positioned within the maximum range of the first device; receiving the data at the third device and storing the data in a memory of the third device; moving the third device to a physical location within the maximum range of the second device; and transmitting, by the third device, the data to the second device.

To provide a tire internal pressure management device, a tire internal pressure management program, and a tire internal pressure management method capable of predicting appropriate internal pressure filling timing even when tire temperature greatly changes, for tires of mobile bodies including aircraft and vehicles.SOLUTION: A tire internal pressure management device includes: a data acquisition unit 102 for acquiring internal pressure time-series data and temperature time-series data for each tire 10 mounted on one of mobile objects M1 including aircraft and vehicles; a representative value calculation unit 103 for calculating a representative value of temperature-corrected internal pressure data for each predetermined period on the basis of the acquired internal pressure time-series data and temperature time-series data; and internal pressure filling timing predicting unit 104 that predicts, as internal pressure filling timing, timing when the internal pressure falls below a predetermined threshold value, on the basis of transition of the calculated representative value of the internal pressure data.SELECTED DRAWING: Figure 1

The invention belongs to the technical field of sensors, and particularly relates to a passive NFC aircraft tire temperature and pressure composite sensor system which comprises a filler neck, a rear cover, a pressure core, a conversion circuit board, a conditioning circuit board assembly and a tag antenna assembly. The filler neck is a two-stage step column; the small-diameter end of the filler neck is provided with an air inlet, and the large-diameter end is provided with a cavity; the pressure core body is arranged in the air inlet hole; the pressure core body is connected with the conversion circuit board; the conversion circuit board is connected with the conditioning circuit board assembly; the conditioning circuit board assembly is fixed on the step surface of the cavity at the large-diameter end of the filler neck through a supporting screw; the tag antenna assembly is installed on the supporting screws through the fixing screws. The rear cover is screwed at the large-diameter end of the filler neck; the small-diameter end of the filler neck is connected with a tire through external threads.

Disclosed is a computer-implemented method of predicting tire pressure of a tire of an aircraft, the method including obtaining first data indicative of an inflation pressure of the tire, obtaining second data indicative of a brake temperature of a brake associated with an aircraft wheel to which the tire is mounted, obtaining third data indicative of a gas temperature of the tire, and obtaining fourth data indicative of one or more predicted operational conditions of the aircraft during a future time period. The method includes determining, based at least in part on the first, second, third and fourth data, predicted tire pressure characteristics of the tire during the future time period.

A computer-implemented method comprising determining, based on a first signal indicative of a pressure in a tire of a wheel of an aircraft and a second signal indicative of a deformation of the tire, a determined load on the wheel, and causing an action to be performed based on the determined load on the wheel. Also a system for an aircraft, the system comprising a monitoring system configured to detect pressure and deformation of a tire of a wheel of the aircraft, and a controller configured to determine, on the basis of the pressure and deformation detected by the monitoring system, load on the wheel.

Disclosed is a method of communicating configuration data of a tire pressure monitoring device configured to be affixed to a wheel in use. The method includes, at the tire pressure monitoring device, receiving (102) a request to confirm configuration data, and responsive to receipt of the request to confirm configuration data, transmitting (104) a configuration data signal which encodes the configuration data. The configuration data signal is configured to be received and understood by a human.

A pneumatic tire (10) is disclosed comprising a carcass (22) and a belt structure (40). The belt structure (40) comprises a plurality of belt layers that include at least one spiral belt layer (60) and at least one zigzag belt layer (70). Each of the at least one spiral belt layers (60) has cords arranged at an angle of 5° or less with respect to an equatorial plane of the pneumatic tire (10) and each of the at least one zigzag belt layers (70) has cords arranged at an angle in a range of from of 2° to 40°, alternatively from 5° to 30°, with respect to the equatorial plane of the pneumatic tire (10) and extending in alternation to turnaround points at each lateral edge of the belt structure (40). A first belt layer of the plurality of belt layers located radially outward of the carcass (22) is one of the at least one spiral belt layers (60). The first belt layer has an axial width less than the axially widest belt layer of the plurality of belt layers. The pneumatic tire (10) further comprises a tread (20) comprising two or more main grooves (17a, 19a, 17b, 19b) extending circumferentially continuously around the pneumatic tire (10) and defining a plurality of ribs (25a, 23a, 21, 23b, 25b) that include an axially outermost rib (25a, 25b) on each lateral side of the tread (20). At 10% to 100% of the rated inflation pressure of the pneumatic tire (10) and no load, each of the two axially outermost ribs (25a, 25b) is radially raised in relation to a respective next nearest rib (23a, 23b) located axially inward of the respective axially outermost rib (25a, 25b).

The present invention relates to a method for monitoring operating parameters of aircraft tires comprising the following steps: E1) pairing transmission modules with wheel positions of the aircraft so as to obtain a mapping associating the transmission modules with wheel positions; E2) storing the resulting mapping; E3) transmitting data comprising a piece of information identifying the transmission module, as well as values of tire operating parameters measured by a sensor; E4) verifying the existence of an association between the information identifying the transmission module and a wheel position on a given aircraft within the mapping so as to ensure that the information received belongs to the given aircraft; E5) displaying the operating parameter values as well as the wheel on which this at least one operating parameter value was measured.

The invention relates to a device (100) for measuring the pressure of a tyre (2) mounted on a rim (1), comprising: - a valve (110) mounted on the rim (1) and comprising a first channel (112), a pin (115) mounted so as to be translationally movable in the first channel between an opening position and a blocking position; - an intermediate body (120) which is mounted on the valve and which defines a second channel (122) that extends the first channel and receives an attachment rod ((113300)) for attaching the intermediate body to the valve, the attachment rod having a first end suitable for bringing the pin from the blocking position into the opening position, and an intermediate portion that blocks the second channel; - a pressure sensor (140) accommodated in a third channel of the intermediate body that opens into the second channel; and - retaining means (150) for retaining the pressure sensor in the third channel of the intermediate body.

This invention relates to a radial aircraft tire crown belt structure and a radial aircraft tire. The radial aircraft tire crown belt structure includes: a reinforcing ply, a carcass layer, and a crown region; the reinforcing ply includes: a first belt layer, a second belt layer, and a third belt layer. In this embodiment, the first belt strip is wound circumferentially at a near-zero angle in a spiral manner. The circumference of each layer is set to s*n+(1 / 6-1 / 2)n, that is, the first layer of the layered structure is wound from point O to point D in a second direction, and then wound for n / 4 more to reach point F. Then, the second layer of the layered structure is wound from point F in the opposite direction to the second direction to point G. Then, the third layer of the layered structure is wound sequentially from point G to point H in an axial direction. The fourth layer of the layered structure is wound from point H to point O. This configuration of the first belt layer allows for a more uniform width of the first belt layer wound at each position in the carcass layer, making the first belt layer more stable in terms of stress and other aspects.

The invention relates to a rod (20) for a pneumatic tire (10), comprising: at least one strand of glass fiber embedded in an organic matrix, wherein the diameter D of the rod (20) is from 14 to 25 mm and wherein the breaking strength (Fm) of the rod (20) is greater than or equal to 150 kN. Figure for abbreviation: Fig. 2

A wheel assembly is provided that includes a structure defining a wheel portion configured to receive a portion of a tire. The wheel assembly further includes a structure of the wheel portion defining an air channel from a face of the wheel portion to an area that receives the portion of the tire, an end of the air channel proximate to the face being configured to receive a valve, where the structure is further configured to receive a corrosion mitigation device within the air channel.

In a radial tire for aircraft according to this disclosure, in a tire widthwise cross-sectional view, in a reference state assembled onto an applicable rim, charged with a prescribed internal pressure, and unloaded, a rim width RW of the applicable rim and a tire maximum width W satisfy RW / W≤0.7, and in the tire widthwise cross-sectional view, in the reference state, a tread width TW and the tire maximum width W satisfy 0.73<TW / W<0.8.

A method of communicating configuration data of a tire pressure monitoring device configured to be affixed to a wheel in use. The method includes, at the tire pressure monitoring device, receiving a request to confirm configuration data, and responsive to receipt of the request to confirm configuration data, transmitting a configuration data signal which encodes the configuration data. The configuration data signal is configured to be received and understood by a human. The configuration data signal is indicative of any of an aircraft wheel location at which the tire pressure monitoring device is intended to be located, and a security code representative of security parameters of the tire pressure monitoring device.

The present disclosure provides an inflation system for inflating inflatable objects, such as aircraft tires. The inflation system includes a flow sensor arranged to sense a flow rate of pressurized air supplied to an inflatable object by way of a supply path. The inflation system also includes a computing system. The computing system is configured to inflate, using feedback from the flow sensor, the inflatable object with a learned volume of pressurized air specific to the inflatable object.

A tire (100) is disclosed comprising a tread (12), a carcass having at least one ply (2A-2F), preferably a plurality of plies (2A-2F) such as three six carcass plies, wound about a pair of bead cores (33), and a crown reinforcement or belt structure (10). The tire (100) further comprises at least one breaker layer (200) radially inside the tread (12). The at least one breaker layer (200) is formed of monofilaments (201) inclined at an angle in a range of from 0 degrees to + / - 10 degrees relative to the equatorial plane (CL) of the tire (100). Preferably, the tire (100) is a tire designed for use under heavy loads and high speeds and / or is an aircraft tire. Preferably, the at least one breaker layer (200) is a cut and puncture resistant breaker layer (200).

Disclosed is an aircraft wheel 20 comprising a tyre 4 and a heater mechanism, the heater mechanism comprising a heater 22 that is configured to heat a gas enclosed by the tyre to increase pressure of the gas. Also disclosed are an aircraft tyre pressure control system, and a method of controlling pressure of a gas enclosed by a tyre of an aircraft wheel. The heater mechanism may be attached to either the wheel rim 2 or be integral to the tyre and may be controlled wirelessly through two communication interfaces 202, 104. The heater mechanism may also include an energy harvester 110.

Disclosed is a method of exchanging cryptographic parameters in a network of tire monitoring devices, the method including broadcasting, from each tire monitoring device to a plurality of other tire monitoring devices, a message comprising a cryptographic parameter generated by that respective tire monitoring device.

The invention provides a tire dismounting device and a using method thereof, and belongs to the technical field of aviation technology comprehensive guarantee, and the portable tire dismounting device comprises a bottom plate, a fixing shaft, a fixing plate, a pressing plate and an operating rod; wherein the bottom plate is fixedly screwed with the fixing shaft, the fixing plate is fixedly screwed at the other end of the fixing shaft, one end, close to the fixing plate, of the fixing shaft is provided with a single-lug connector which is used for being hinged with a double-lug connector on an operating rod through a hinge, the operating rod can be manually operated to apply pressure downwards conveniently, and the pressing plate is sleeved on the operating rod. The device adopts a combined design, and has better manufacturability and bearing capacity; the tire dismounting device is simple in structure, capable of completing tire dismounting work without an external power source and convenient to carry outside.

The invention provides a pneumatic tire having a tire tread with a ground engaging outer surface. The tread further has a first or central tread zone located on the central or crown portion of the tread and formed of a first rubber compound. Additionally, the tread has a second or shoulder tread zone located axially outward of the first or central tread zone on each lateral end of the tread. The second or shoulder tread zone is formed of a second rubber compound. In one example, the first rubber compound has a G′ (at 50% strain) in the range of 1.6 to 1.8 MPa. In another example, the second rubber compound has a G′ (at 100% strain) in the range of 800 to 830 KPa.

A method, apparatus and system are disclosed in which an indication given by at least one tyre monitoring device is confirmed by input received from another source is disclosed. The method includes causing, by the control device, at least one tyre monitoring device mounted on a wheel to measure a tyre pressure and to indicate a status using an indicator provided on the tyre monitoring device; receiving, from the at least one tyre monitoring device, data representative of the status of the at least one tyre monitoring device; receiving input representative of the status indicated on the indicator of the at least one tyre monitoring device; comparing the received data representative of the status with the received input representative of the status; and taking action based on the result of the comparing.

The present disclosure provides an inflation system (100) for inflating an inflatable object, such as an aircraft tire (104). The inflation system (100) includes a flow sensor (118) arranged to sense a flow of pressurized air supplied to the inflatable object through a supply path (112). The inflation system (100) also includes a computing system (130). The computing system (130) is configured to use feedback from the flow sensor (118) to inflate the inflatable object with an acquired volume (148) of pressurized air specific to the inflatable object.

The present invention relates to an aircraft tire in which the tread comprises a composition based on at least one elastomeric matrix comprising from 20 to 100 phr of isoprene elastomer and from 0 to 80 phr of a styrene-butadiene copolymer; a reinforcing filler mainly comprised of carbon black; from 1 to 30 phr of at least one hydrocarbon resin mainly composed of units from aromatic and cycloaliphatic monomers; and a crosslinking system.

Disclosed is an apparatus for monitoring the condition of a pneumatic tyre. The apparatus comprises at least one pressure sensor to measure an internal pressure within the tyre. At least one speed sensor is provided to measure a rotational speed of the tyre. A controller is configured to receive data from the pressure sensor and the speed sensor and output indications related to a condition of the tyre. The controller determines the output indications by tracking the internal pressure with respect to time during use of the tyre, identifying at least one change in internal tyre pressure in a time interval. The time interval is between a first reference time and a second reference time, the reference times corresponding to points at which the speed sensor indicates different rotational speeds of the tyre. The controller further monitors the pressure change as a function of rotational speed of the tyre to provide an indicator of tyre condition. A method of monitoring wear in a pneumatic tyre.

The invention discloses an aircraft tire vulcanization simulation method, device, equipment and medium, and relates to the technical field of tire vulcanization simulation, the method comprises the following steps: dividing the vulcanization reaction of an aircraft tire into a plurality of key modules, and constructing a vulcanization reaction kinetic model, a vulcanization reaction heat generation model and a dynamic thermophysical parameter model based on the key modules; obtaining a to-be-processed tire model and vulcanization reaction parameters; coupling the vulcanization reaction kinetic model, the vulcanization reaction heat generation model and the dynamic thermophysical parameter model, and dynamically simulating the whole vulcanization process of the tire model to be treated according to vulcanization reaction parameters to obtain a simulation result. According to the method, the whole vulcanization dynamic process of the to-be-processed tire model can be more comprehensively and accurately restored, and the accuracy of simulation result determination is greatly improved.

The present invention discloses a portable helicopter tire changer, which relates to the technical field of aviation equipment; the equipment includes an upper limit mechanism, a hollow hydraulic lifting mechanism, a central spindle, a hydraulic pump and a downward pressure mechanism; it is mainly used in scenarios where a helicopter stays in an unsecured outdoor location and needs to temporarily change a tire. The equipment has a small structure size, light weight, and can be disassembled and packed, making it convenient to carry with a vehicle or carry randomly; the rod system mechanism used in the equipment can be universally applicable to tires of different diameters, and a balance rod mechanism is designed to ensure that the downward pressure seat maintains its posture. The tire changer of the present invention can be used to conveniently, quickly and effectively realize helicopter tire changes.

An aircraft tire (T) has a pair of bead sections (100), sidewall sections (104) extending from outer side in a radial direction of the bead sections, and a tread section (106) extending between the sidewall sections; the aircraft tire includes an RFID tag (10) having a tag main body (IC chip) (11) configured to store an information about the aircraft tire and an antenna (A1, A2) extended from the tag main body, wherein, when a diameter size of the aircraft tire is 15 inches or less, in a tread surface view, the antenna is disposed such that the antenna is parallel to a tire circumferential direction or intersects the tire circumferential direction within a predetermined angle range, and a belt part (103) disposed in the tread section (106) is made of non-metal material.

Disclosed is a tire monitoring device including a pressure sensor, an accelerometer, a gyroscope, and a wireless communication interface. The pressure sensor is for sensing an internal pressure of a tire of an aircraft wheel. The accelerometer is for sensing an acceleration of the tire monitoring device. The gyroscope is for sensing an angular velocity of the tire monitoring device. The wireless communication interface is for wirelessly communicating a signal based on at least one of a sensed internal pressure sensed by the pressure sensor, a sensed acceleration sensed by the accelerometer, and a sensed angular velocity sensed by the gyroscope.