Abstract: Systems and methods for moving a vehicle component relative to the vehicle, the system including first and second upwardly-extending supports; a lift frame between the first and second supports including a crossbeam, and a pair of cambered truss assemblies secured to the crossbeam and configured to be attached to the vehicle component; movable first and second crossbeam support assemblies on the first and second supports to support the rotation of the crossbeam; a first lift mechanism configured to move the first crossbeam support assembly along the first support in response to a first control signal; a rotational drive mechanism configured to rotate the crossbeam relative to the first and second crossbeam support assemblies in response to a second control signal; and an electronic controller configured to generate the first and second control signals to change the position of the vehicle component relative to the vehicle.

Abstract: Positioning system and method for positioning engine components on an aircraft, the system including a moveable support for the engine component, a laser assembly, and a system controller. First and second lasers of the laser assembly align their respective beams with an engine target position on the aircraft and provide an indication of a first angle of the first laser beam to a reference line, and an indication of a second angle of the second laser beam to the reference line; and the system controller is configured to rotate the moveable support to rotationally position the engine component, determine the vertical distance between the engine component and the target position based at least in part on the first and second angles, and to control a lift mechanism to reduce the vertical distance between the engine component and the engine.

Abstract: Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide system structured to removably couple to a first aircraft structure having a first hinge component. A second guide system is structured to removably couple to a second aircraft structure having a second hinge component. The first guide system is to engage the second guide system to enable alignment between the first hinge component and the second hinge component during assembly of the first aircraft structure and the second aircraft structure.

Abstract: A fire extinguisher system. The system includes a first fire extinguisher containing a first agent that is suitable for extinguishing fire, the first fire extinguisher having a first discharge port for discharging the first agent therethrough, and a first actuator for actuating the first discharge port. The system also includes a second, similar fire extinguisher. The system also includes a valve coupled to the first discharge port via a first line and coupled to the second discharge port via a second line, wherein the valve is configured to release the first agent and the second agent into a third line. The system also includes a controller connected to the first actuator and the second actuator, the controller configured to activate the first actuator and the second actuator in a predetermined sequence.

Abstract: A ventilation closure system includes a damper, a shape memory alloy actuator, and a heating device. The shape memory alloy actuator is coupled to the damper. The shape memory alloy actuator has a first state in which the damper is positioned to permit airflow in the duct and has a second state in which the damper is positioned to obstruct the airflow in the duct. The shape memory alloy actuator is configured to change from the first state to the second state responsive to the shape memory alloy actuator attaining a first temperature responsive to heat released by an exothermic reaction in a compartment associated with the duct. The heating device is configured to heat the shape memory alloy actuator to maintain the damper in a position that obstructs the airflow in the duct.

Abstract: Positioning system and method for positioning engine components on an aircraft, the system including a moveable support for the engine component, a laser assembly, and a system controller. First and second lasers of the laser assembly align their respective beams with an engine target position on the aircraft and provide an indication of a first angle of the first laser beam to a reference line, and an indication of a second angle of the second laser beam to the reference line; and the system controller is configured to rotate the moveable support to rotationally position the engine component, determine the vertical distance between the engine component and the target position based at least in part on the first and second angles, and to control a lift mechanism to reduce the vertical distance between the engine component and the engine.

Abstract: Systems and methods for moving a vehicle component relative to the vehicle, the system including first and second upwardly-extending supports; a lift frame between the first and second supports including a crossbeam, and a pair of cambered truss assemblies secured to the crossbeam and configured to be attached to the vehicle component; movable first and second crossbeam support assemblies on the first and second supports to support the rotation of the crossbeam; a first lift mechanism configured to move the first crossbeam support assembly along the first support in response to a first control signal; a rotational drive mechanism configured to rotate the crossbeam relative to the first and second crossbeam support assemblies in response to a second control signal; and an electronic controller configured to generate the first and second control signals to change the position of the vehicle component relative to the vehicle.

Abstract: A ventilation closure system includes a damper, a shape memory alloy actuator, and a heating device. The shape memory alloy actuator is coupled to the damper. The shape memory alloy actuator has a first state in which the damper is positioned to permit airflow in the duct and has a second state in which the damper is positioned to obstruct the airflow in the duct. The shape memory alloy actuator is configured to change from the first state to the second state responsive to the shape memory alloy actuator attaining a first temperature responsive to heat released by an exothermic reaction in a compartment associated with the duct. The heating device is configured to heat the shape memory alloy actuator to maintain the damper in a position that obstructs the airflow in the duct.

Abstract: A system, apparatus, and method for testing a squib circuit. An electrical signature of the squib circuit is monitored when a test switch in the squib circuit is activated. The electrical signature of the squib circuit is based on characterizing resistors electrically connected to squibs in the squib circuit in which each characterizing resistor in the characterizing resistors has a resistance value. A health of each squib in the squib circuit is determined based on the electrical signature of the squib circuit.

Abstract: An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft forward of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.

Abstract: A system, apparatus, and method for testing a squib circuit. An electrical signature of the squib circuit is monitored when a test switch in the squib circuit is activated. The electrical signature of the squib circuit is based on characterizing resistors electrically connected to squibs in the squib circuit in which each characterizing resistor in the characterizing resistors has a resistance value. A health of each squib in the squib circuit is determined based on the electrical signature of the squib circuit.

Abstract: A fire extinguisher system. The system includes a first fire extinguisher containing a first agent that is suitable for extinguishing fire, the first fire extinguisher having a first discharge port for discharging the first agent therethrough, and a first actuator for actuating the first discharge port. The system also includes a second, similar fire extinguisher. The system also includes a valve coupled to the first discharge port via a first line and coupled to the second discharge port via a second line, wherein the valve is configured to release the first agent and the second agent into a third line. The system also includes a controller connected to the first actuator and the second actuator, the controller configured to activate the first actuator and the second actuator in a predetermined sequence.

Abstract: An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft forward of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.

Abstract: An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft aft of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.

Abstract: A method and apparatus for heating a surface of an aircraft. A flow of air is received from a portion of an engine in a tube system. The air flowing through the tube system is heated. The air is sent to the surface of the aircraft. The flow of the air from the portion of the engine and the heating system to heat the surface of the aircraft are controlled. Icing conditions at the surface of the aircraft are reduced.

Abstract: Concepts and technologies are disclosed herein for a sensor system for detecting, characterizing, monitoring, and analyzing data. According to some embodiments disclosed herein, a monitoring system is configured to obtain data from a sensor system. The sensor system includes two or more sensors and can indicate an operating state detected at a monitored structure by the sensors. The monitoring system also obtains operational data including a threshold value for the sensors and an expected value for the sensors. The monitoring system is configured to adjust the thresholds based, at least partially, upon the operational data to obtain an adjusted threshold value, and to compare the data value to the adjusted threshold. The monitoring system can determine if the monitored structure is operating in an alarm condition.

Abstract: A method and apparatus for heating a surface of an aircraft. A flow of air is received from a portion of an engine in a tube system. The air flowing through the tube system is heated. The air is sent to the surface of the aircraft. The flow of the air from the portion of the engine and the heating system to heat the surface of the aircraft are controlled. Icing conditions at the surface of the aircraft are reduced.

Abstract: Concepts and technologies are disclosed herein for a sensor system for detecting, characterizing, monitoring, and analyzing data. According to some embodiments disclosed herein, a monitoring system is configured to obtain data from a sensor system. The sensor system includes two or more sensors and can indicate an operating state detected at a monitored structure by the sensors. The monitoring system also obtains operational data including a threshold value for the sensors and an expected value for the sensors. The monitoring system is configured to adjust the thresholds based, at least partially, upon the operational data to obtain an adjusted threshold value, and to compare the data value to the adjusted threshold. The monitoring system can determine if the monitored structure is operating in an alarm condition.