Abstract: An access panel to be received in an access aperture in a lower skin of a wing on an aircraft incorporates a body surrounded by a sealing flange. The body is configured to be received in the access aperture and the sealing flange is configured to be received on a sealing land surrounding the access aperture. An integral heat exchanger extends from a top surface of the body into a fuel tank in the wing to conduct heat from the fuel to an external surface of the access panel.

Abstract: An example robotic system includes (a) a housing having a first surface, (b) one or more sensors coupled to the housing, (c) a first wheel and a second wheel coupled to and extending away from the housing, (d) a motor configured to drive at least one of the first wheel and the second wheel, and (e) data storage including program instructions stored thereon that when executed by one or more processors of the robotic system while operating in an environment, cause the robotic system to perform operations comprising: (i) controlling the motor to cause the robotic system to navigate on a surface within the environment based, (ii) detecting, using the one or more sensors, an object approaching the robotic system and responsively controlling the motor to cause the robotic system to cease movement, and (iii) retracting the first wheel and the second wheel into the housing.

Abstract: A system includes a signal generator that is configured to generate a first electrical signal. The system also includes a light source configured to generate a light beam based on the first electrical signal. The light source is also configured to direct the light beam towards a structural member of an aircraft. The system also includes a photoelectric sensor configured to receive a reflected light beam and convert the reflected light beam to a second electrical signal. The reflected light beam corresponds to a portion of the light beam that is reflected from one or more optical reflectors coupled to the structural member. The system also includes circuitry configured to estimate a location of a center-of-gravity of the aircraft based on a timing difference between the first electrical signal and the second electrical signal.

Abstract: An example robotic system includes (a) a housing having a first surface, (b) one or more sensors coupled to the housing, (c) a first wheel and a second wheel coupled to and extending away from the housing, (d) a motor configured to drive at least one of the first wheel and the second wheel, and (e) data storage including program instructions stored thereon that when executed by one or more processors of the robotic system while operating in an environment, cause the robotic system to perform operations comprising: (i) controlling the motor to cause the robotic system to navigate on a surface within the environment based, (ii) detecting, using the one or more sensors, an object approaching the robotic system and responsively controlling the motor to cause the robotic system to cease movement, and (iii) retracting the first wheel and the second wheel into the housing.

Abstract: A system includes a signal generator that is configured to generate a first electrical signal. The system also includes a light source configured to generate a light beam based on the first electrical signal. The light source is also configured to direct the light beam towards a structural member of an aircraft. The system also includes a photoelectric sensor configured to receive a reflected light beam and convert the reflected light beam to a second electrical signal. The reflected light beam corresponds to a portion of the light beam that is reflected from one or more optical reflectors coupled to the structural member. The system also includes circuitry configured to estimate a location of a center-of-gravity of the aircraft based on a timing difference between the first electrical signal and the second electrical signal.

Abstract: In a particular implementation, a method includes generating an initial weight estimate associated with an aircraft based on a reference operational empty weight (OEW) and at least one of a latitude or an altitude of the aircraft at a first location. The reference OEW is predetermined at a second location that is distinct from the first location. The method includes determining an additional load capability of the aircraft based on a difference between the initial weight estimate and the reference OEW. The method further includes generating an output that indicates the additional load capability.

Abstract: In a particular implementation, a method includes generating an initial weight estimate associated with an aircraft based on a reference operational empty weight (OEW) and at least one of a latitude or an altitude of the aircraft at a first location. The reference OEW is predetermined at a second location that is distinct from the first location. The method includes determining an additional load capability of the aircraft based on a difference between the initial weight estimate and the reference OEW. The method further includes generating an output that indicates the additional load capability.