mhurhangee/ep-ind-claims huggingface dataset:
A length-adjustable connecting rod (10, 30) for a reciprocating piston engine, in particular for a reciprocating piston internal combustion engine, wherein the connecting rod (10, 30) comprises at least one first connecting rod part and one second connecting rod part, wherein the second connecting rod part has a section with a guide cylinder on its end facing the first connecting rod part, wherein the first connecting rod part has a guide shank corresponding in form to the guide cylinder on its end facing the second connecting rod part, wherein the guide shank of the first connecting rod part is at least partly accommodated by the guide cylinder in a functional state of use of the connecting rod (10, 30) and is movable relative to same, in particular along a longitudinal axis of the connecting rod (10, 30), for adjusting an effective length of the connecting rod, wherein the first connecting rod part comprises a first stop surface and the second connecting rod part a second stop surface, and wherein the first stop surface lying against the second stop surface restricts a relative movement between the first connecting rod part and the second connecting rod part in a first direction, wherein the connecting rod (10, 30) is designed such that when the first stop surface lies against the second stop surface, at least a portion of compressive force acting on the connecting rod (10, 30) along the longitudinal axis of the connecting rod is transferred past the guide shank via the first stop surface and the second stop surface from the first connecting rod part into the second connecting rod part and/or vice versa, characterized in that an effective length of the guide shank relative to a depth of the guide cylinder is dimensioned such that when the effective connecting rod length is being shortened, an end of the guide shank facing the second connecting rod part first bottoms with the guide cylinder and afterwards the first stop surface bottoms with the second stop surface. wherein the connecting rod (10, 30) is designed such that when the first stop surface lies against the second stop surface, at least a portion of compressive force acting on the connecting rod (10, 30) along the longitudinal axis of the connecting rod is transferred past the guide shank via the first stop surface and the second stop surface from the first connecting rod part into the second connecting rod part and/or vice versa, characterized in that an effective length of the guide shank relative to a depth of the guide cylinder is dimensioned such that when the effective connecting rod length is being shortened, an end of the guide shank facing the second connecting rod part first bottoms with the guide cylinder and afterwards the first stop surface bottoms with the second stop surface.
A method for manufacturing or adapting a batch of electronic devices, comprising: causing a first predetermined event to be performed for each of the batch of electronic devices by a first manufacturer or first adapter; storing a first event attestation in each of the batch of electronic devices, the first event attestation comprising a cryptographically authenticated attestation to the occurrence of the first predetermined event, wherein the first event attestation is signed using a first cryptographic key associated with the first manufacturer or first adapter; causing a second predetermined event to be performed for each of the batch of electronic devices by a second manufacturer or second adapter; and storing a second event attestation in each of the batch of electronic devices, the second event attestation comprising a cryptographically authenticated attestation to the occurrence of the second predetermined event, wherein the second event attestation is signed using a second cryptographic key associated with the second manufacturer or second adapter; wherein the first event attestation is cryptographically authenticated using the same first cryptographic key for each of the batch of electronic devices, and the second event attestation is cryptographically authenticated using the same second cryptographic key for each of the batch of electronic devices, and wherein the first manufacturer or first adapter is different from the second manufacturer or second adapter. causing a first predetermined event to be performed for each of the batch of electronic devices by a first manufacturer or first adapter; storing a first event attestation in each of the batch of electronic devices, the first event attestation comprising a cryptographically authenticated attestation to the occurrence of the first predetermined event, wherein the first event attestation is signed using a first cryptographic key associated with the first manufacturer or first adapter; causing a second predetermined event to be performed for each of the batch of electronic devices by a second manufacturer or second adapter; and storing a second event attestation in each of the batch of electronic devices, the second event attestation comprising a cryptographically authenticated attestation to the occurrence of the second predetermined event, wherein the second event attestation is signed using a second cryptographic key associated with the second manufacturer or second adapter; wherein the first event attestation is cryptographically authenticated using the same first cryptographic key for each of the batch of electronic devices, and the second event attestation is cryptographically authenticated using the same second cryptographic key for each of the batch of electronic devices, and wherein the first manufacturer or first adapter is different from the second manufacturer or second adapter.
An internal combustion engine having a system for utilising the waste heat from the internal combustion engine via the Clausius-Rankine cycle process, the system comprising - a circuit having lines with a working medium, in particular water, for forming the system, - a working medium pump for delivering the working medium, - a vaporiser-exhaust gas heat exchanger and a vaporiser-EGR heat exchanger for heating and/or vaporising the liquid working medium with the exhaust gas, - an expander, - a condenser for liquefying the vaporous working medium, - preferably a collecting and equalising tank for the liquid working medium, wherein the line for the working medium is run from the condenser to the vaporiser-EGR heat exchanger, so that the working medium after flowing through the condenser first flows through the vaporiser-EGR heat exchanger and the line for the working medium is run from the vaporiser-EGR heat exchanger to the vaporiser-exhaust gas heat exchanger, so that the working medium after flowing through the vaporiser-EGR heat exchanger first flows through the vaporiser-exhaust gas heat exchanger, characterised in that the exhaust gas through the vaporiser-EGR heat exchanger has temperatures in the range from 500 to 700°C and the exhaust gas through the vaporiser-exhaust gas heat exchanger has temperatures in the range from 280 to 380°C. - a circuit having lines with a working medium, in particular water, for forming the system, - a working medium pump for delivering the working medium, - a vaporiser-exhaust gas heat exchanger and a vaporiser-EGR heat exchanger for heating and/or vaporising the liquid working medium with the exhaust gas, - an expander, - a condenser for liquefying the vaporous working medium, - preferably a collecting and equalising tank for the liquid working medium, wherein the line for the working medium is run from the condenser to the vaporiser-EGR heat exchanger, so that the working medium after flowing through the condenser first flows through the vaporiser-EGR heat exchanger and the line for the working medium is run from the vaporiser-EGR heat exchanger to the vaporiser-exhaust gas heat exchanger, so that the working medium after flowing through the vaporiser-EGR heat exchanger first flows through the vaporiser-exhaust gas heat exchanger, characterised in that the exhaust gas through the vaporiser-EGR heat exchanger has temperatures in the range from 500 to 700°C and the exhaust gas through the vaporiser-exhaust gas heat exchanger has temperatures in the range from 280 to 380°C.
A computing device, comprising: An application-specific integrated circuit, ASIC, operable to be connected to a camera by a first bus, the ASIC configured to identify, from an image acquired using the camera, an area of interest in the image, the ASIC being further configured to perform image computational processing to generate machine vision information based on the area of interest, wherein the machine vision information can be used to control a user interface of the device; and a general purpose processor connected to the ASIC by a second bus, the general purpose processor being configured to receive, from the ASIC, the machine vision information, wherein. in response to an amount of processing by the ASIC satisfying a predetermined threshold, the ASIC is configured to initiate the transfer of a portion of the image corresponding to the area of interest to the general purpose processor, and the general purpose processor being further configured to perform at least one process on the portion of the image corresponding to the area of interest. An application-specific integrated circuit, ASIC, operable to be connected to a camera by a first bus, the ASIC configured to identify, from an image acquired using the camera, an area of interest in the image, the ASIC being further configured to perform image computational processing to generate machine vision information based on the area of interest, wherein the machine vision information can be used to control a user interface of the device; and a general purpose processor connected to the ASIC by a second bus, the general purpose processor being configured to receive, from the ASIC, the machine vision information, wherein. in response to an amount of processing by the ASIC satisfying a predetermined threshold, the ASIC is configured to initiate the transfer of a portion of the image corresponding to the area of interest to the general purpose processor, and the general purpose processor being further configured to perform at least one process on the portion of the image corresponding to the area of interest.
An observation system comprising: a light source section for emitting illuminating light; and an image pickup section for detecting reflected light from an object in a body, the object being illuminated with the illuminating light, to pick up an image of the object; and wherein the light source section is configured such that the illuminating light has a light intensity peak in a wavelength range of 400 nm - 450 nm in which a first optical absorption peak of oxygenated hemoglobin is included, and a light intensity in a wavelength range of 460 nm - 500 nm is 20% - 70% relative to the light intensity peak. a light source section for emitting illuminating light; and an image pickup section for detecting reflected light from an object in a body, the object being illuminated with the illuminating light, to pick up an image of the object; and wherein the light source section is configured such that the illuminating light has a light intensity peak in a wavelength range of 400 nm - 450 nm in which a first optical absorption peak of oxygenated hemoglobin is included, and a light intensity in a wavelength range of 460 nm - 500 nm is 20% - 70% relative to the light intensity peak.
A method for identifying objects of interest during an air search and rescue, SAR, operation, comprising: detecting an object of interest with a sensor onboard an aircraft, where the object of interest is located near an SAR pattern of an aircraft; displaying a sensor image of the object of interest on a visual display system; inputting the location of the object of interest into the visual display system located onboard the aircraft, where the location of the object is translated as latitude, longitude and altitude from data from the sensor and the sensor image; automatically adding a distinct symbol at the input location on the visual display system (400, 500) that categorizes the object of interest as a probable object; selecting the object of interest on the visual display system based on the sensor image, where the object of interest is selected by an aircrew member; confirming the distinct symbol accurately categorizes the selected object of interest as a probable object or rejecting the categorization of the distinct symbol as a probable object, where the distinct symbol is confirmed or rejected by the aircrew member, and wherein a probable object symbol is changed to an object found symbol when the distinct symbol is confirmed as accurately categorizing the object of interest as a probable object by the aircrew member; and transmitting contents of the visual display system with the distinct symbols to a ground-based controller, an aircraft coordinator, or to other aircraft participating in the SAR operation. detecting an object of interest with a sensor onboard an aircraft, where the object of interest is located near an SAR pattern of an aircraft; displaying a sensor image of the object of interest on a visual display system; inputting the location of the object of interest into the visual display system located onboard the aircraft, where the location of the object is translated as latitude, longitude and altitude from data from the sensor and the sensor image; automatically adding a distinct symbol at the input location on the visual display system (400, 500) that categorizes the object of interest as a probable object; selecting the object of interest on the visual display system based on the sensor image, where the object of interest is selected by an aircrew member; confirming the distinct symbol accurately categorizes the selected object of interest as a probable object or rejecting the categorization of the distinct symbol as a probable object, where the distinct symbol is confirmed or rejected by the aircrew member, and wherein a probable object symbol is changed to an object found symbol when the distinct symbol is confirmed as accurately categorizing the object of interest as a probable object by the aircrew member; and transmitting contents of the visual display system with the distinct symbols to a ground-based controller, an aircraft coordinator, or to other aircraft participating in the SAR operation.
A hatch operating mechanism arranged to control opening and closing movements of a hatch (202; 302; 402) covering an opening in a vehicle the mechanism comprising; - a first and a second arm (211, 221; 311, 321; 411, 421), which are rotatably attached to the vehicle at a first end and rotatably attached onto the hatch at a second end; characterized in - that a first and a second connecting element (214, 224; 314, 324; 414, 424) are arranged extending between and displaceable relative to a pair of spaced apart, parallel guide means (216, 226, 217, 227; 316, 317; 416, 417) fixed to the hatch (202; 302; 402), wherein the second ends of the first and second arms (211, 221; 311, 321; 411, 421) are rotatably attached to a respective first and second connecting element (214, 224; 314, 324; 414, 424), - that the first and the second arm (211, 221; 311, 321; 411, 421) are located in mirrored positions relative to a plane of symmetry at right angles to the guide means (216, 226, 217, 227; 316, 317; 416, 417); - that the first ends of the arms (211, 221; 311, 321; 411, 421) are arranged in a common plane, which first ends have axes arranged at equal and opposite angles relative the plane of symmetry; that the first and second arms (211, 221; 311, 321; 411, 421) are simultaneously rotatable in opposite directions about their first ends over an arcuate path; and that the connecting elements (214, 224; 314, 324; 414, 424) are arranged to execute a reciprocating movement along the guide means (216, 226; 217, 227) during the rotation of the first and second arms over the arcuate path. - a first and a second arm (211, 221; 311, 321; 411, 421), which are rotatably attached to the vehicle at a first end and rotatably attached onto the hatch at a second end; - that a first and a second connecting element (214, 224; 314, 324; 414, 424) are arranged extending between and displaceable relative to a pair of spaced apart, parallel guide means (216, 226, 217, 227; 316, 317; 416, 417) fixed to the hatch (202; 302; 402), wherein the second ends of the first and second arms (211, 221; 311, 321; 411, 421) are rotatably attached to a respective first and second connecting element (214, 224; 314, 324; 414, 424), - that the first and the second arm (211, 221; 311, 321; 411, 421) are located in mirrored positions relative to a plane of symmetry at right angles to the guide means (216, 226, 217, 227; 316, 317; 416, 417); - that the first ends of the arms (211, 221; 311, 321; 411, 421) are arranged in a common plane, which first ends have axes arranged at equal and opposite angles relative the plane of symmetry;
An aircraft landing gear attachment comprising: an aircraft mount (106,108); a trunnion block; characterised by a reaction block in abutment with, but detached from, the trunnion block; in which the trunnion block is connected to the mount by a first frangible connection (140,142), and in which the reaction block is connected to the mount by a second frangible connection such that a force applied to the trunnion block in a first direction towards the reaction block separates the trunnion block and the mount at a first predetermined force level by rupturing the first and second frangible connections, and a force applied to the trunnion block in a second different direction different to the first direction separates the trunnion block and the mount at a second, lower, predetermined force level by rupturing the first frangible connection but not the second frangible connection. an aircraft mount (106,108); a trunnion block; characterised by a reaction block in abutment with, but detached from, the trunnion block; in which the trunnion block is connected to the mount by a first frangible connection (140,142), and in which the reaction block is connected to the mount by a second frangible connection such that a force applied to the trunnion block in a first direction towards the reaction block separates the trunnion block and the mount at a first predetermined force level by rupturing the first and second frangible connections, and a force applied to the trunnion block in a second different direction different to the first direction separates the trunnion block and the mount at a second, lower, predetermined force level by rupturing the first frangible connection but not the second frangible connection.
Method for producing a weather and corrosion resistant reflector for electromagnetic radiation, in particular for infrared radiation, visible light and ultraviolet radiation, having a high overall reflectivity, comprising a reflector body made from aluminium or an aluminium alloy with a reflective surface, wherein the surface of the reflector body is pretreated with anodised aluminium that is produced directly from the aluminium present on the surface of the reflector body and has a pretreatment layer, wherein the reflector includes an external, terminating, transparent protective layer from a sol-gel varnish having a network of polyoxysilanes, on which the pretreatment layer is produced, including the following method steps: a) hydrolysing a mixture of a solution A containing alkoxysilanes and a solution B containing colloidally dissolved Ti02 particles or colloidally dissolved Ti02 and Si02 particles; or hydrolysing a mixture of a solution A containing alkoxysilanes and a solution B containing colloidal silica, and admixing Ti02 particles to the hydrolysed mixture; b) applying the hydrolysed mixture onto the free surface of the reflector body; c) curing and drying the sol-gel varnish layer; d) etching the sol-gel varnish layer in order to expose the Ti02 particles on the surface of the protective layer, so that a) the surface of the protective layer is at least partially covered with free Ti02 particles for generating a self-cleaning effect, b) the Ti02 particles are present in the anatase modification and confer hydrophilic properties to the surface of the protective layer. a) hydrolysing a mixture of a solution A containing alkoxysilanes and a solution B containing colloidally dissolved Ti02 particles or colloidally dissolved Ti02 and Si02 particles; or hydrolysing a mixture of a solution A containing alkoxysilanes and a solution B containing colloidal silica, and admixing Ti02 particles to the hydrolysed mixture; b) applying the hydrolysed mixture onto the free surface of the reflector body; c) curing and drying the sol-gel varnish layer; d) etching the sol-gel varnish layer in order to expose the Ti02 particles on the surface of the protective layer, a) the surface of the protective layer is at least partially covered with free Ti02 particles for generating a self-cleaning effect, b) the Ti02 particles are present in the anatase modification and confer hydrophilic properties to the surface of the protective layer.
A refuse landfill impervious system capable of prolonging breakdown time of leachate, comprising a leachate collection and drainage layer, a first HDPE geomembrane impervious layer, a clay layer and a groundwater collection and drainage layer which are sequentially stacked from top to bottom, and the clay layer comprises a lower clay layer, a middle clay layer and an upper clay layer which are sequentially arranged, wherein the middle clay layer is filled with a medium-fine sand layer laid with sands of particle sizes ranging from 0.1mm to 0.5 mm and water contents no more than 3%, so that the saturated permeability coefficient of the medium-fine sand layer varies from 1×10 -5 to 1×10 -3 cm/s.