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 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: 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.