The landing gear for a Piper Cub® light aircraft, comprises at least two wheels, is attached to a part of the fuselage in front of the center of gravity, and has a fixed tubular reinforcement that is generally triangular in shape, of which the apex is turned downwards, the ends of the base of the reinforcement and the apex of same being coupled, with articulation capability, to a suspension system linked to the wheels. Each end of the base of the reinforcement is angularly coupled to a wheel, by means of a damping member, while the apex of said reinforcement is coupled symmetrically to each of the wheels, by means of a connecting rod.

The landing gear for a Piper Cub® light aircraft, comprises at least two wheels, is attached to a part of the fuselage in front of the center of gravity, and has a fixed tubular reinforcement that is generally triangular in shape, of which the apex is turned downwards, the ends of the base of the reinforcement and the apex of same being coupled, with articulation capability, to a suspension system linked to the wheels. Each end of the base of the reinforcement is angularly coupled to a wheel, by means of a damping member, while the apex of said reinforcement is coupled symmetrically to each of the wheels, by means of a connecting rod.

The invention provides a firefighting float plane having a fuselage and two floats mounted to the fuselage. The fuselage has a water tank with open and closed configurations. In some embodiments, the water tank is integrated into the fuselage, and/or both the water tank and the fuselage have a generally triangular cross-sectional configuration. The water tank has a closed bottom in its closed configuration and an open bottom in its open configuration. In some embodiments, the plane has specified ratio of water tank holding capacity to total power of two engine assemblies. It can optionally also have the above-noted fuselage configuration, tank configuration, or both. In some embodiments, the plane has dual propellers, two engine assemblies, and two tail booms, optionally together with specified ratio of water tank holding capacity to total power of two engine assemblies. It may also have the above-noted fuselage configuration, tank configuration, or both.

The invention provides a firefighting float plane having a fuselage and two floats mounted to the fuselage. The fuselage has a water tank with open and closed configurations. In some embodiments, the water tank is integrated into the fuselage, and/or both the water tank and the fuselage have a generally triangular cross-sectional configuration. The water tank has a closed bottom in its closed configuration and an open bottom in its open configuration. In some embodiments, the plane has specified ratio of water tank holding capacity to total power of two engine assemblies. It can optionally also have the above-noted fuselage configuration, tank configuration, or both. In some embodiments, the plane has dual propellers, two engine assemblies, and two tail booms, optionally together with specified ratio of water tank holding capacity to total power of two engine assemblies. It may also have the above-noted fuselage configuration, tank configuration, or both.

An information processing device (10) includes a sensing section (140) that senses a pressure variation of a fluid filling a deformable filled section (130) that is provided to a portion of a leg of a mobile body (100) that is in either a contact state or a non-contact state at which portion the leg contacts an external environment, and a determining section (150) that determines a state of the leg of the mobile body (100) on the basis of the pressure variation of the fluid sensed by the sensing section (140).

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

A UAV and its power system, and a system for minimizing UAV failure. The UAV power system has a propulsion propeller, which is arranged at the rear end of the UAV; the traction propeller which is arranged at the front end of the UAV; either the traction propeller or the propulsion propeller is the main propeller while the other is the backup one; when the UAV is in the level flight stage, at least one of the traction propeller and the propulsion propeller is in the working state; and the driving component which is used to drive the propulsion propeller and the traction propeller. The UAV power system provided by the disclosure is provided with a traction propeller and a propulsion propeller, respectively, to improve the failure redundancy and reduce the safety deficiency of the probability of common mode failure (CMF).