An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor. The payload rail allows mechanical connection of payloads to the fuselage and positioning of the payloads such that a center of gravity of the payloads is alignable with the axis of rotation.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body including an outer surface and an inner surface, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, one or more receiving structures positioned on the outer surface of the central body and configured to receive one or more electrical components, the one or more electrical components comprising at least a battery of the UAV, and an indicator light disposed at an opening or a window on one of the plurality of branch members, wherein the opening or the window is made of a transparent or semi-transparent material.

A rotorcraft having an airframe, the airframe carrying at least one rotor that contributes to providing the rotorcraft with lift and/or propulsion, the rotorcraft having at least one undercarriage. The at least one undercarriage comprises at least one inclined wheel undercarriage, the inclined wheel undercarriage having an undercarriage leg carrying at least one axle, the at least one axle carrying at least one wheel, the at least one wheel not being in contact with any other wheel, the at least one wheel presenting positive or negative camber when the at least one wheel touches the ground and independently of forces exerted by said airframe on the inclined wheel undercarriage.

A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor. The payload rail allows mechanical connection of payloads to the fuselage and positioning of the payloads such that a center of gravity of the payloads is alignable with the axis of rotation. A system for controlling the unmanned helicopter includes a processor and a memory for providing instructions to the processor. The processor can receive a task, dynamically determine a route for the task and autonomously perform the task including flying along at least part of the route. The route is based on the task, geography and terrain.

Aspects of the subject technology relate to a landing gear of a rotorcraft including two skid tubes and a cross tube. The cross tube couples the skid tubes to each other and attaches the skid tubes to a fuselage of the rotorcraft. At least a part of the cross tube is made of a composite material to achieve sufficient absorption of energy while preventing the fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition. The rotorcraft includes the landing gear to achieve sufficient absorption of energy while preventing the fuselage from coming into contact with the ground surface, at the time of landing the rotorcraft, under a more satisfactory condition.

A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

A landing assembly and method of landing an aircraft. The landing assembly includes a landing gear, a charging circuit, a sampling circuit and a processor. The charging circuit applies a charge to the landing gear and the sampling circuit measures a discharge rate of the electrical charge from the landing gear. The processor determines a contact between the landing gear and a surface from the discharge rate.

Various implementations directed to composite skid member with varying cross-sections are provided. In one implementation, an aircraft landing gear assembly may include two composite skid members configured to contact the ground, where each composite skid member includes a first cross-section and a second cross-section, and where the first cross-section is different than the second cross-section. The aircraft landing gear assembly may also include two cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two composite skid members.

A base attachment module (BAM) of a small aerial vehicle (SAV) for attaching the SAV to an unprepared work surface has a surface meeting docking assembly (DA) with contact points for contacting the work surface, and a contracting suction cup (CSC) in a position surrounded by the contact points such that it extends beyond a plane (or other surface contour) of the points in a fully extended operating position, and is retracted below the plane in a retracted position. Actuation of the CSC when in contact with the surface, allows for the DA to be brought into contact with the contact points in a controlled manner, for a high stiffness attachment, as is needed for deployment of robotic tasks from a SAV.