A hover-capable flying machine such as a drone includes a robotic arm extending from the body, and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm. In embodiments, the end of the arm is equipped with a balancing rotor assembly that may provide lift sufficient to counteract the weight of the payload and/or of the arm. In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and/or extending beyond the machine in a direction generally opposite to the extended arm. The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency.

Methods and apparatus for reducing energy consumed by drones during flight are disclosed. A drone includes a housing, a motor, and a route manager to generate a route for a flight of the drone based on wind data. The wind data includes turbine-generated wind data provided by turbines that detect airflows received at the turbines. The turbines are located in an area within which a segment of the flight of the drone is to occur. The route is to be followed by the drone during the flight to reduce energy consumed by the drone during the flight.

The invention relates to an assembly (10) comprising a launch motor vehicle (12) and a drone (14), the launch motor vehicle (12) being capable of travelling on a launch track to exceed a given speed threshold relative to a surrounding air mass, the launch motor vehicle (12) being provided with a launch ramp (20) cooperating with the drone (14) to, in a launching position, guide the drone (14) from a starting position in a launch direction to the front of the launch motor vehicle (12). The drone (14) comprises one or more reactors (30) and does not comprise a landing gear.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

Disclosed is a remotely controlled wireless drone which employs a solid fuel rocket engine to propel it quickly to a desired or location. More specifically, an unmanned vehicle including a fuselage and a propulsion unit engaged with the fuselage, the propulsion unit being operable to bring the unmanned vehicle to a desired altitude or location, generally during a launch stage. The fuselage also includes multiple rotors pivotally engaged with the fuselage and a rotor positioning system operable to pivot the multiple rotors between stowed and deployed positions. The stowed position of the propellers minimizes drag and instability during the launch stage, and the deployed position allows the multiple rotors to control the position and altitude of the unmanned vehicle after the fuel of the rocket engine is spent. Submersible/amphibious and other embodiments are also described.

Methods of powering a heat engine with a remote lasers are disclosed, where the ambient air surrounding the engine is used as the working fluid. All methods include inputting the ambient air into the engine, absorbing laser optical radiation, turning it into heat, supplying the heat to the air, harvesting mechanical work from expanding air and releasing the air back into surrounding atmosphere.

A multi-hybrid aircraft engine that includes a primary compressor 1, a multiplier 199 comprising a drive block, a driven block, driven block pistons 54, and primary shafts 78 and 41; an output shaft 105, and a speed regulator 167. The multi-hybrid aircraft engine is configured such that the primary compressor 1 is fluidly connected to the drive block 46 which is mechanically connected to the driven block 57. The primary compressor 1 pumps compressible fluid to the drive block 46 through the speed regulator 167 to drive the drive block 46, which in turn, drives the primary shafts 78 and 41. The primary shafts 78 and 41 drive the driven block 57, which pumps fluid via the driven block pistons 54, to the drive block 46 through the speed regulator 167 to increase the flow rate of compressible fluid within the multi-hybrid aircraft engine. Furthermore, the driven block 57 provides a shaft 68 that is connected to sets of planetary gears 62 connected to an output shaft 105 that drives a propeller 186.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.