Systems, methods, and apparatus are disclosed for generating power for a vehicle. Apparatus may include a power generator configured to generate power based on one or more aerodynamic forces associated with a vehicle. The power generator may be further configured to be deployed from a first portion of the vehicle. The apparatus may also include a flow control device configured to generate an increase in airflow associated with the power generator. The increase in airflow enables, at least in part, the generation of additional power by the power generator. The flow control device may be further configured to be deployed from a second portion of the vehicle.

A wing with slipstream turbine comprising: a wing or airfoil and at least one turbine, wherein wing or airfoil has at least one partial cylindrical void in a surface and at least one turbine is partially encapsulated within partial cylindrical void. Optionally, wing with slipstream turbine may further comprise at least one slipstream outrigger to help focus the flow of the slipstream more directly on a turbine. Optionally, wing with slipstream turbine may further comprise at least one lateral outrigger to create a low-pressure area which functions to add additional energy transfer to turbine. Optionally, wing with slipstream turbine may further comprise two leading outriggers to help focus the flow of the slipstream more directly on a turbine. Optionally, wing or airfoil may further comprise a leading subcomponent, a left subcomponent, and a right subcomponent to create a super low-pressure area which functions add additional energy transfer to turbine.

A motor control topology relevant to airborne wind turbines and a control process for such a motor control topology is disclosed herein. A system may include an aerial vehicle that may include a plurality of propellers, a plurality of drive units coupled to the plurality of propellers, and a tether. Each drive unit may include a motor/generator and a motor controller. The plurality of drive units may include at least two pairs of drive units that include a first drive-unit pair and a second drive-unit pair. The drive units in each drive pair may be connected in parallel, and the at least two pairs of drive units may be connected in series. The drive units may be configured to operate in a first mode and operate in a second mode.

A turbine mounted behind an aircraft wing provides a specified proportion of a propulsive force in the aircraft flight direction to an amount of power generated by the turbine when driven by the airflow trailing the wing. The turbine converts a portion of the otherwise wasted energy in the rotational vortices trailing the aircraft wing into thrust that reduces aircraft drag while also providing electricity to power electrical systems on the aircraft. In one embodiment, the method used to construct the turbine saves computation time by using an optimization routine to define a preliminary turbine configuration based on an idealized vortex model and then matches it to the flow trailing an actual aircraft wing. The method is also capable of modeling a turbine construction that will use the energy in the wake solely to generate electricity without increasing drag on the aircraft or solely to reduce drag without generating electricity.

An apparatus, including a vertex rotor. The apparatus includes a transmission system, with the transmission system connected to the vertex rotor. The apparatus includes a drive shaft, with the drive shaft connected to the transmission system. The apparatus includes a first bevel gear and a second bevel gear. The first bevel gear and the second bevel gear are connected to the drive shaft.

A drone with a horizontal rotor includes one or more rotor(s) (115, 116) which rotate in a horizontal plane, each rotor (115, 116) being equipped with one or more rigid or non-rigid blades (120, 121), the blade end being mounted on an electric motor (110, 111) with a propeller.

A method of using a bagged power generation system comprising windbags and water-bags for harnessing wind and water power to produce electricity to meet the escalating energy needs of mankind. Windbags integrated with aerodynamically shaped inflatable bodies filled with lighter-than-air gas: HAV, UAV, airplanes; enabling the apparatus to attain high altitude to capture and entrap high velocity wind. Water-bags integrated with hydrodynamic shaped bodies HUV, UUV, Submarine-boats; enabling the apparatus to dive, capture and entrap swift moving tidal-currents. Attached tether-lines pulling on the rotating reel-drums and generators to produce electricity. Active control surfaces, turbo-fans, propellers provide precision control of the apparatus. A system configured to maximize fluids capture, retention and optimized extraction of its kinetic energy. An extremely scalable and environmentally friendly method, system, apparatus, equipment and techniques configured to produce renewable green energy with high productivity and efficiency.

A passive vehicle drag reduction system including an airflow capture inlet, a flow consolidating conduit, an air driven rotor assembly, and one or more flow exhaust conduits. The airflow capture inlet defines an airflow capture inlet direction. The flow consolidating conduit is close sided. The air driven rotor assembly has a rotor assembly inlet and an air driven rotor. The rotor assembly inlet defines a rotor airflow inlet direction. The air driven rotor has a laterally extending rotation axis transverse to the rotor airflow inlet direction and one or more air redirecting blades defining one or more rotor airflow outlet directions substantially parallel to the rotation axis. Each of the one or more flow exhaust conduits has a redirecting exhaust outlet located laterally of the air driven rotor assembly. The redirecting exhaust outlet defines an exhaust outlet airflow direction that is substantially parallel to the airflow capture inlet direction.

A passive vehicle drag reduction system including an airflow capture inlet, a flow consolidating conduit, an air driven rotor assembly, and one or more flow exhaust conduits. The airflow capture inlet defines an airflow capture inlet direction. The flow consolidating conduit is close sided. The air driven rotor assembly has a rotor assembly inlet and an air driven rotor. The rotor assembly inlet defines a rotor airflow inlet direction. The air driven rotor has a laterally extending rotation axis transverse to the rotor airflow inlet direction and one or more air redirecting blades defining one or more rotor airflow outlet directions substantially parallel to the rotation axis. Each of the one or more flow exhaust conduits has a redirecting exhaust outlet located laterally of the air driven rotor assembly. The redirecting exhaust outlet defines an exhaust outlet airflow direction that is substantially parallel to the airflow capture inlet direction.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.