Abstract: An internal combustion engine generally includes at least a cylinder; at least an intake valve acting on an intake port for controlling the airflow entering the cylinder; at least an injector for supplying uncombusted fuel to the cylinder; at least an outlet valve acting on a respective outlet port for controlling the flow of the exhaust gases at the outlet of the cylinder; a piston sliding in a linear manner within the cylinder; at least a first spark plug arranged in a position adjacent to the injector and acting within the combustion chamber; a pre-chamber communicating with the combustion chamber; and a second spark plug acting within the pre-chamber; the first spark plug is arranged in an intermediate position between the pre-chamber and the injector.

Abstract: A process to adjust the ignition timing of an air-fuel mixture in a combustion chamber of an internal combustion engine, the process comprises determining a first quantity indicative of a pressure of the mixture for a cycle of the engine, determining a second quantity indicative of a speed of the engine, determining a third quantity indicative of a first temperature of a conditioning fluid, providing a heat exchange mathematical model for the combustion chamber, which maps the three quantities from the first to the third one onto a fourth quantity indicative of a second temperature of a wall portion around the combustion chamber, estimating the fourth quantity by means of the three determined quantities and by means of the mathematical model, and adjusting the ignition timing as a function of the fourth estimated quantity.

Abstract: A fire hose reeling system includes a support frame that is positionable on a ground surface. The support frame has a first lateral edge and a second lateral edge. A reel apparatus is mounted on the support frame. The reel apparatus releasably engages a fire hose and forms the hose into a roll when the reel apparatus is actuated. A stabilizing panel has a perimeter edge pivotally coupled to the support frame such that the stabilizing panel is positionable in an upright position defining a stored position or in deployed position extending away from the first lateral edge. When in the deployed position, the stabilizing panel abuts the ground surface and is stepped upon while the reel apparatus is used to stabilize the assembly.

Abstract: A fire hose reeling system includes a support frame that is positionable on a ground surface. The support frame has a first lateral edge and a second lateral edge. A reel apparatus is mounted on the support frame. The reel apparatus releasably engages a fire hose and forms the hose into a roll when the reel apparatus is actuated. A stabilizing panel has a perimeter edge pivotally coupled to the support frame such that the stabilizing panel is positionable in an upright position defining a stored position or in deployed position extending away from the first lateral edge. When in the deployed position, the stabilizing panel abuts the ground surface and is stepped upon while the reel apparatus is used to stabilize the assembly.

Abstract: A process to adjust the ignition timing of an air-fuel mixture in a combustion chamber of an internal combustion engine, the process comprises determining a first quantity indicative of a pressure of the mixture for a cycle of the engine, determining a second quantity indicative of a speed of the engine, determining a third quantity indicative of a first temperature of a conditioning fluid, providing a heat exchange mathematical model for the combustion chamber, which maps the three quantities from the first to the third one onto a fourth quantity indicative of a second temperature of a wall portion around the combustion chamber, estimating the fourth quantity by means of the three determined quantities and by means of the mathematical model, and adjusting the ignition timing as a function of the fourth estimated quantity.

Abstract: The exemplary embodiments relate to improving the user experience associated with a digital platform. A first user device configured to remotely access a digital platform may receive a first signal broadcast by a second user device. Two or more types of communication protocols that are available to use for establishing a direct communication channel between the user devices are identified. One of the communication protocols is selected and a communication channel is established between the user devices in accordance with the selected communication protocol. The first user device then receives authentication information from the second user and establishes a session with the digital platform based on the authentication information received from the second user device.

Abstract: The exemplary embodiments relate to improving the user experience associated with a digital platform. A first user device configured to remotely access a digital platform may receive a first signal broadcast by a second user device. Two or more types of communication protocols that are available to use for establishing a direct communication channel between the user devices are identified. One of the communication protocols is selected and a communication channel is established between the user devices in accordance with the selected communication protocol. The first user device then receives authentication information from the second user and establishes a session with the digital platform based on the authentication information received from the second user device.

Abstract: An aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: According to one embodiment, an aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: According to one embodiment, an aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: An internal combustion engine comprising: at least a cylinder; at least an intake valve acting on an intake port for controlling the airflow entering the cylinder; at least an injector for supplying uncombusted fuel to the cylinder; at least an outlet valve acting on a respective outlet port 18 for controlling the flow of the exhaust gases at the outlet of the cylinder; a piston sliding in a linear manner within the cylinder; at least a first spark plug arranged in a position adjacent to the injector and acting within the combustion chamber; a pre-chamber communicating with the combustion chamber; and a second spark plug acting within the pre-chamber; the first spark plug is arranged in an intermediate position between the pre-chamber and the injector.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: According to one embodiment, an aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.