A system and method for dynamically updated vehicle navigation planning for a second UV based on navigation feedback of a first UV. The first UV navigates based on a first navigation plan and the second UV navigates based on a second navigation plan. The system includes: a processing circuitry; and a memory, the memory containing instructions that, when executed by the processing circuitry, configure the system to: receive the navigation feedback of the first UV, wherein the navigation feedback of the first UV includes telemetry data indicating at least a divergence event and a location of the divergence event, wherein the divergence event is a divergence of the first UV from the first navigation plan; and dynamically update the second navigation plan based on the navigation feedback of the first UV when the second navigation plan includes the location of the divergence event.

An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; and a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135.

This data processing device is provided with: an acceleration acquisition unit that acquires the acceleration of a moving body equipped with a mechanism for generating a propulsion force and equipped with a measuring instrument for measuring the strength of at least a one-direction component of the wind to which the moving body is exposed; a wind information acquisition unit that acquires wind information indicating the blowing direction of the wind and the strength of the wind, both of which are identified from the values measured by the measuring instrument; an external force estimation unit that estimates, on the basis of the acceleration and the direction and magnitude of the propulsion force, the magnitude of an external force exerted by the wind on the moving body; and a generation unit that generates relational information indicating the relation between the wind strength and the estimated magnitude of the external force.

An aerial vehicle control system includes an aerial vehicle and a computing device. The aerial vehicle includes an altitude controller and a lateral propulsion controller. The computing device includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the computing device to obtain location data corresponding to a location of the aerial vehicle; obtain wind data; determine an altitude command, a latitude command, and a longitude command based on at least one of the location data or the wind data; cause the altitude controller to implement at least one of the altitude command, the latitude command, or the longitude command; and cause the lateral propulsion controller to implement at least one of the altitude command, the latitude command, or the longitude command.

An aerial vehicle control system includes an aerial vehicle and a computing device. The aerial vehicle includes an altitude controller and a lateral propulsion controller. The computing device includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the computing device to obtain location data corresponding to a location of the aerial vehicle; obtain wind data; determine an altitude command, a latitude command, and a longitude command based on at least one of the location data or the wind data; cause the altitude controller to implement at least one of the altitude command, the latitude command, or the longitude command; and cause the lateral propulsion controller to implement at least one of the altitude command, the latitude command, or the longitude command.

An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

Using a set of airflow sensors disposed on an airfoil of an aircraft, first airflow data including an amount of airflow experienced at each airflow sensor at a first time is measured. Using a trained neural network model, the first airflow data is analyzed to determine an airflow state of the aircraft. In response to determining that the aircraft is in the abnormal airflow state, a control surface and a power unit of the aircraft are adjusted. Responsive to the adjusting, the aircraft is returned to the normal airflow state.

A tether compensated unmanned aerial vehicle (UAV) is described. In one embodiment, the UAV includes a winch with a tether to lower an item from the UAV for delivery, a tether compensation mechanism configured to contact the tether as it extends from the winch, and a flight controller to control a flight path of the UAV. The flight controller is also configured to direct the tether compensation mechanism to clamp the tether based on the flight path of the UAV. Further, based on movement identified in the tether using a sensor, a tether response controller can determine a complementary response and direct the tether compensation mechanism to brace the tether against the movement. Thus, the tether compensation mechanism can help stabilize sway or movement in the tether, which can help prevent the tether from undesirable swinging.

An imaging system that includes a camera mounted on an aerial platform, for example a balloon, allows a user to increase the longevity of the camera's battery by remote control. A user may capture imagery at a time scale of interest and desired power consumption by adjusting parameters for image capture by the camera. A user may adjust a time to capture an image, a time to capture a video, or a number of cycles per time period to capture one or more images as the aerial platform moves in a region of interest to change power consumption for imaging. The system also provides imaging alignment to account for unwanted movement of the aerial platform when moved in the region of interest. Additionally, a mounting device is provided that is simple and inexpensive, and that allows a camera to remain positioned in a desired position relative to the ground.