An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle includes a funnel, a hose and a thrust producing device. Thrust producing device includes a main body that is rigidly attached to the funnel, and at least two rotors that are connected to the main body for producing thrust. The thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe.

According to an embodiment of the disclosure, there is provided a drone control system in which the drone user may directly adjust the torque required in the flight environment, that is, the torque required by the drone motor, with the transmitter control when controlling the transmitter stick. According to an embodiment, a drone control system comprises a flight controller receiving a stick control value from a transmitter, converting the stick control value into a motor speed value, and outputting the motor speed value and an electronic speed controller receiving the motor speed value from the flight controller, converting the motor speed value into a motor torque value, converting the motor torque value into a power driving value, and outputting the power driving value to a motor.

The present invention relates to a system and method to facilitate remote and accurate maneuvering of unmanned aerial vehicle (UAV) under communication latency. The UAV provides a ground control station (GCS), with a video feed of an area of interest (AOI), after a time T from actual capturing of the video by the UAV, due to latency in video and communication between the UAV and the GCS. The GCS further receives control commands directly from a controller of the user, and transmit the video feed along with interactive marker(s), step by step marking of singular points using raycast vector, and/or virtual UAV being overlaid on top of the video feed to a display module or VR headset associated with the user, to facilitate the user to assess how much movement the user is exerting on the UAV through the controller, and also see how the actual UAV will perform or maneuver in the AOI after time T, thereby facilitating the user to continuously assess and rectify maneuvering or directing of the UAV in the AOI.

A rotor system has a mast axis, a first rotor rotatable about the mast axis in a first direction and the first rotor has a first number of first rotor blades, and a second rotor rotatable about the mast axis in a second direction and the second rotor has a second number of second rotor blades that is different than the first number. The second direction is opposite the first direction.

A rotor system has a mast axis, a first rotor rotatable about the mast axis in a first direction and the first rotor has a first number of first rotor blades, and a second rotor rotatable about the mast axis in a second direction and the second rotor has a second number of second rotor blades that is different than the first number. The second direction is opposite the first direction.

A method for controlling an unmanned aerial vehicle within a flight operating space. The unmanned aerial vehicle includes one or more sensor arrays on each spar. The method includes determining, using a plurality of sensor arrays, a flight path for the unmanned aerial vehicle. The method also includes receiving, by at least one sensor array of the plurality of sensor arrays, sensor data identifying at least one object in the operating space. The sensor data is transmitted over a communications bus connecting components of the UAV. The method further includes determining, by one or more processors onboard the unmanned aerial vehicle, a flight path around the at least one object. The method also includes generating, by the one or more onboard processors, a first signal to cause the unmanned aerial vehicle to navigate within the operating space around the at least one object.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.

An unmanned aerial vehicle according to the present invention may comprise: a rotor-blade for providing thrust according to generation of main stream; and a safety guard disposed to surround the rotor-blade. The safety guard may comprise: a guide member which is disposed coaxially with the rotor-blade while having a gap between the guard member and the end of the rotor-blade, so as to stabilize, when the rotor-blade rotates, a flow field suctioned by a negative pressure, and stably boost a discharge flow when the pressure is changed to a positive pressure; and a diffuser which is disposed coaxially with and radially spaced apart from the guide member, and generates a secondary flow toward the main stream to increase a flow rate.

The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

A ducted fan drone has a plurality of bent tube propulsors that enshroud rotating fan blades in a manner the eliminates contact with the blades during operation, thereby allowing drone operation in confined areas without risk of injury to people, animals, objects, or the drone itself by incidental contact with the rotating fan blades. The bent tube propulsors have an air passage, an air inlet into the air passage, and an air exit out of the air passage. The air passage has an upwardly bent portion relative to a longitudinal axis of the ducted fan drone, a downwardly bent portion relative to the longitudinal axis, and horizontal section extending between the upwardly and downwardly bent portions. A fan propulsor is disposed within the air passage of each bent tube propulsor at a position along the horizontal section.