A system is provided. The system includes a camera on a refueling aircraft to obtain an image of a receiver aircraft having a receptacle for refueling the receiver aircraft. The system also includes a processor on the refueling aircraft to determine an orientation and position of the receiver aircraft relative to the camera, a separation distance and respective positions of a refueling boom of the refueling aircraft and the receptacle. The processor also generates a display of a side perspective view of 3D models of the refueling boom and the receiver aircraft having the receptacle. The display of the side perspective view illustrates a current position of the refueling boom relative to a current position of the receptacle and enables an operator on the refueling aircraft to observe and guide the refueling boom to the receptacle.

Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

A capture-and-release aircraft for capturing and releasing fixed-wing aircraft is provided. The capture-and-release aircraft comprises a frame to which is secured a set of rotor units. Each rotor unit has a rotor with a rotation axis, the rotation axes of the rotors being generally parallel. A set of aircraft engagement members is also secured to the frame that can align with a set of anchors of a fixed-wing aircraft to releasably couple with the anchors.

A method, apparatus, and computer usable program code for planning refueling. In one advantageous embodiment, the apparatus includes an air refueling plug-in application capable of calculating air refueling routes for a formation of aircraft and a plurality of plug-in applications. A framework capable of providing framework services to the air refueling plug-in application and the plurality of plug-in applications is present. The apparatus also includes a first interface for the air refueling plug-in application and the plurality of plug-in applications to receive the framework services from the framework. The apparatus also has a second interface for the air refueling plug-in application and plurality of plug-in applications to provide services from one plug-in application to another plug-in application. The first interface and the second interface are independent of the air refueling plug-in application and plurality of plug-in applications.

A method, apparatus, and computer usable program code for planning refueling. In one advantageous embodiment, the apparatus includes an air refueling plug-in application capable of calculating air refueling routes for a formation of aircraft and a plurality of plug-in applications. A framework capable of providing framework services to the air refueling plug-in application and the plurality of plug-in applications is present. The apparatus also includes a first interface for the air refueling plug-in application and the plurality of plug-in applications to receive the framework services from the framework. The apparatus also has a second interface for the air refueling plug-in application and plurality of plug-in applications to provide services from one plug-in application to another plug-in application. The first interface and the second interface are independent of the air refueling plug-in application and plurality of plug-in applications.

Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

An aircraft includes an airframe having an extending tail, and a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly. A translational thrust system is positioned at the extending tail and providing translational thrust to the airframe. An active vibration control (AVC) system is located and the airframe and includes a plurality of AVC actuators configured to generate forces to dampen aircraft component vibration, and an AVC controller configured to transmit control signals to the plurality of AVC actuators thereby triggering force generation by the plurality of AVC actuators. A method of damping vibration of an aircraft includes receiving a vibration signal at an AVC controller, communicating a control signal from the AVC controller to a plurality of AVC actuators, generating a force at the AVC actuators, and damping vibration of the aircraft via the generated force.

A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.

A system for detecting a sensor fault of an aerial refueling boom. The system comprises a data collector configured to receive sensor data from a plurality of sensors and determine an aerial refueling boom elevation angle of the aerial refueling boom based on the sensor data, wherein the sensor data comprises at least one of cable length data, a dynamic pressure data or aerial refueling boom position data. The system further comprises a processing unit configured access a database table in a storage unit to determine an estimated aerial refueling boom elevation angle, a comparator configured to compare the estimated aerial refueling boom elevation angle to the determined aerial refueling boom elevation angle, and a fault detector configured to generate a sensor fault signal based on the comparison.

A system for detecting a sensor fault of an aerial refueling boom. The system comprises a data collector configured to receive sensor data from a plurality of sensors and determine an aerial refueling boom elevation angle of the aerial refueling boom based on the sensor data, wherein the sensor data comprises at least one of cable length data, a dynamic pressure data or aerial refueling boom position data. The system further comprises a processing unit configured access a database table in a storage unit to determine an estimated aerial refueling boom elevation angle, a comparator configured to compare the estimated aerial refueling boom elevation angle to the determined aerial refueling boom elevation angle, and a fault detector configured to generate a sensor fault signal based on the comparison.