Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned below the engine and oriented in a upward-facing direction. The nozzle has at least one opening that is closed by a spring-loaded valve.

Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned below the engine and oriented in a upward-facing direction. The nozzle has at least one opening that is closed by a spring-loaded valve.

Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.

Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.

Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.

Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.

Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.

Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.

Abstract: The present application relates to a regenerative or hybrid drive system for an aircraft. The drive system includes the use of a power augmentation device to selectively engage the drive system of an aircraft to store power. The power in the power augmentation device being configured to release a power burst to systems within the aircraft to perform critical flight maneuvers.

Abstract: The present application relates to a regenerative or hybrid drive system for an aircraft. The drive system includes the use of a power augmentation device to selectively engage the drive system of an aircraft to store power. The power in the power augmentation device being configured to release a power burst to systems within the aircraft to perform critical flight maneuvers.

Abstract: A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.