Abstract: The present invention comprises methods and apparatuses for sensing attributes of an aircraft and efficiently communicating relevant attributes to a pilot. The invention allows a state of the aircraft to be determined, and then used to control systems, configure displays, select checklists relevant to the determined state, and automatically respond to emergencies based on the aircraft state. Embodiments of the invention can use the determined state of the aircraft to monitor and control electrical sensors and system as appropriate for the determined state; to communication information relevant to the determined state to a pilot (e.g., by displaying gauges in a manner and priority specific to the determined state); and to display contextually-relevant checklists (e.g., displaying a checklist of actions necessary for an aircraft in the determined state).

Abstract: The present invention provides systems and methods for controlling the speed of flap retraction on aircraft, and alerts to the pilot of potentially unsafe flap position. The invention accepts direction from a pilot and senses operation of the aircraft to determine appropriate flap position and flap retraction speed.

Abstract: The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.

Abstract: A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.

Abstract: A switching and fault detection circuit comprises two controllable switches capable of coupling a power source to a load. A controller can control the switches and test them for faults, and a voltage sensor can read the output voltage going to the load. Dual-redundant switches and fault detection circuitry can provide correct operation if one should fail. Control and feedback logic can determine if each of the solid-state switches is operating correctly during the power-on and power-off cycles and can also check for a fail-open condition during normal operations. If it is determined that a solid switch has failed open or closed, a fault can be generated.

Abstract: A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft's engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.

Abstract: A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.

Abstract: The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.

Abstract: The present invention provides systems and methods for controlling the speed of flap retraction on aircraft, and alerts to the pilot of potentially unsafe flap position. The invention accepts direction from a pilot and senses operation of the aircraft to determine appropriate flap position and flap retraction speed.

Abstract: A system comprised of switches, fuses, microprocessor-based monitoring, and a pilot display that provides a method to bypass computer-controlled switching of aircraft power circuits. A backup circuit in addition to the computer-controlled switching circuit provides a method to guarantee power delivery in the case of a failure of the computer-controlled switch. The system provides the pilot with an indication when the backup circuit is engaged. When the other devices are turned off and/or the engine is shut down, an indication can be provided to the pilot that the backup circuit is on. An indication can also be provided to the pilot that the switch is in the off position when it should be on.

Abstract: A switching and fault detection circuit comprises two controllable switches capable of coupling a power source to a load. A controller can control the switches and test them for faults, and a voltage sensor can read the output voltage going to the load. Dual-redundant switches and fault detection circuitry can provide correct operation if one should fail. Control and feedback logic can determine if each of the solid-state switches is operating correctly during the power-on and power-off cycles and can also check for a fail-open condition during normal operations. If it is determined that a solid switch has failed open or closed, a fault can be generated.

Abstract: Methods and apparatuses that control trim of an aircraft even in the presence of conflicting trim inputs, for example by disabling the trim input switches on the aircraft when conflicting switch inputs are received. When conflicting switch inputs are received and certain time conditions are met, the controller can disable the switch inputs and provide a backup and independent means to control the trim circuitry. The pilot can be allowed to re-enable the disabled inputs.

Abstract: A system comprised of switches, fuses, microprocessor-based monitoring, and a pilot display that provides a method to bypass computer-controlled switching of aircraft power circuits. A backup circuit in addition to the computer-controlled switching circuit provides a method to guarantee power delivery in the case of a failure of the computer-controlled switch. The system provides the pilot with an indication when the backup circuit is engaged. When the other devices are turned off and/or the engine is shut down, an indication can be provided to the pilot that the backup circuit is on. An indication can also be provided to the pilot that the switch is in the off position when it should be on.

Abstract: A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft's engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.

Abstract: The present invention comprises methods and apparatuses for sensing attributes of an aircraft and efficiently communicating relevant attributes to a pilot. The invention allows a state of the aircraft to be determined, and then used to control systems, configure displays, select checklists relevant to the determined state, and automatically respond to emergencies based on the aircraft state. Embodiments of the invention can use the determined state of the aircraft to monitor and control electrical sensors and system as appropriate for the determined state; to communication information relevant to the determined state to a pilot (e.g., by displaying gauges in a manner and priority specific to the determined state); and to display contextually-relevant checklists (e.g., displaying a checklist of actions necessary for an aircraft in the determined state).