An experimental bench for an unmanned aerial vehicle (UAV) power system and avionics equipment, which relates to the technical field of UAV test, comprising a support component, a power system load-bearing component, an avionics equipment load-bearing component, a jacking component and a roller component. A plurality of power system load-bearing components are provided, and are fixedly arranged on the support components, respectively, and each power system load-bearing component is configured to carry the power system of a UAV; the avionics equipment load-bearing component is fixedly arranged on the support component, and the avionics equipment load-bearing component is configured to bear the avionics equipment of the UAV; the output end of the jacking component is fixedly connected to the bottom end of the support component.

An experimental bench for an unmanned aerial vehicle (UAV) power system and avionics equipment, which relates to the technical field of UAV test, comprising a support component, a power system load-bearing component, an avionics equipment load-bearing component, a jacking component and a roller component. A plurality of power system load-bearing components are provided, and are fixedly arranged on the support components, respectively, and each power system load-bearing component is configured to carry the power system of a UAV; the avionics equipment load-bearing component is fixedly arranged on the support component, and the avionics equipment load-bearing component is configured to bear the avionics equipment of the UAV; the output end of the jacking component is fixedly connected to the bottom end of the support component.

A method of managing in-service operation of a fleet of aircraft is provided that includes generating a schedule of flights through an air transportation network that includes airports, and that includes direct flight routes or flight connections between the airports. The method includes performing a fleet assignment of the fleet of aircraft to the schedule of flights based on availability metric values for respective aircraft of the fleet of aircraft, and dispatching the fleet of aircraft serve the schedule of flights to according to the fleet assignment. In this regard, performing the fleet assignment includes, for an aircraft of the fleet of aircraft, accessing reliability metric values for parts of the aircraft. Availability scores for the aircraft are determined based on the reliability metric values from respective ones of the data sources, and the availability scores are combined to determine an availability metric value for the aircraft.

A system for monitoring of elastomeric bearings is described. A pattern or shape can be applied to a joint comprising elastomeric material. A camera can be disposed such that it can capture photographs or video of the pattern and how it deforms under torque and other stresses. Actual deformation of the shape/pattern can be compared to an expected deformation to gauge levels of degradation of the elastomeric material or other joint components.

A system for monitoring of elastomeric bearings is described. A pattern or shape can be applied to a joint comprising elastomeric material. A camera can be disposed such that it can capture photographs or video of the pattern and how it deforms under torque and other stresses. Actual deformation of the shape/pattern can be compared to an expected deformation to gauge levels of degradation of the elastomeric material or other joint components.

An aircraft wing inspection system includes a housing, a light source, a camera, and a display device. The housing is adapted to be mounted on an aircraft fuselage. The light source is disposed within the housing and is operable, upon being electrically energized, to emit a light beam. The camera is disposed within the housing and is configured to capture images of the aircraft wing, convert the captured images to digital image data, and transmit the digital image data. The display device is disposed remote from, and is in operable communication with, the camera. The display device is configured to receive the digital image data transmitted from the camera and to render the captured images.

An aircraft wing inspection system includes a housing, a light source, a camera, and a display device. The housing is adapted to be mounted on an aircraft fuselage. The light source is disposed within the housing and is operable, upon being electrically energized, to emit a light beam. The camera is disposed within the housing and is configured to capture images of the aircraft wing, convert the captured images to digital image data, and transmit the digital image data. The display device is disposed remote from, and is in operable communication with, the camera. The display device is configured to receive the digital image data transmitted from the camera and to render the captured images.

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes an aircraft propulsion system component with a leading edge. The aircraft propulsion system assembly also includes artificial ice attached to the aircraft propulsion system component. The artificial ice at least partially covers and extends longitudinally along the leading edge.

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes an aircraft propulsion system component with a leading edge. The aircraft propulsion system assembly also includes artificial ice attached to the aircraft propulsion system component. The artificial ice at least partially covers and extends longitudinally along the leading edge.

An apparatus including a frame forming an interface device configured for connection to a test chassis, and at least one interface connector coupled to the frame, the at least one interface connector corresponding to connectors of a unit under test, the interface device being configured for insertion through one or more sealable apertures of an environmentally protective chassis that houses the test chassis, and coupling to an interface device seating surface of the environmentally protective chassis without any intervening environmental interface or environmental interface plane located between the interface device seating surface and the test chassis, wherein the frame forming the interface device includes a first end plate configured with electrical connectors and mechanical attachment members configured to align and attach a circuit card to the interface device.