An aerial vehicle (10) has an aerial platform (12) that supports lift elements (11), an engine (14) and a fuel supply (15) and that has a coupling mechanism (16) adapted for coupling to a removable load (17). The lift elements include a soft or flexible wing (11) flexibly coupled to the aerial platform at points of suspension on opposite sides of the aerial platform whose location (A, B) relative to a longitudinal axis of the platform is such that the aerial platform and the attached load has a center of gravity (C.G.) which maintains balance of the aerial platform. An adjustment system (18) is coupled to the points of suspension and is operative for moving the points of suspension relative to the longitudinal axis of the platform when cargo is unloaded from the flying platform to preserve balance.

The invention described and claimed in this application is a throttle assembly for a paramotor with an integrated locking mechanism which can be engaged to lock the throttle input in any position to maintain level flight. The throttle locking mechanism can be quickly disengaged as needed by squeezing the throttle control lever. The throttle locking mechanism is also able to be tuned when in the locked position as to attain the ideal engine input for level flight. The throttle locking mechanism can be preset and quickly returned to a designated power setting.

The invention described and claimed in this application is a throttle assembly for a paramotor with an integrated locking mechanism which can be engaged to lock the throttle input in any position to maintain level flight. The throttle locking mechanism can be quickly disengaged as needed by squeezing the throttle control lever. The throttle locking mechanism is also able to be tuned when in the locked position as to attain the ideal engine input for level flight. The throttle locking mechanism can be preset and quickly returned to a designated power setting.

The present invention relates to the field of heavier-than-air aircraft, such as airplanes and unmanned aerial vehicles (UAV) and, in particular, to emergency rescue systems. The technical objective is accomplished by providing an aircraft, such as a drone, including a powerplant, a parachute, and a body. In particular, the parachute has a fixed shape, it is permanently in an opened state and is connected to the body by rigid braces, while the aircraft center of gravity is located below the aircraft aerodynamic center.

The present invention relates to the field of heavier-than-air aircraft, such as airplanes and unmanned aerial vehicles (UAV) and, in particular, to emergency rescue systems. The technical objective is accomplished by providing an aircraft, such as a drone, including a powerplant, a parachute, and a body. In particular, the parachute has a fixed shape, it is permanently in an opened state and is connected to the body by rigid braces, while the aircraft center of gravity is located below the aircraft aerodynamic center.

A paramotor assembly, a unibody frame for such a paramotor assembly, and a method of making a paramotor assembly are provided. The paramotor assembly includes a monolithic, non-metallic molded body, a hoop extending at least partially around the molded body, and spars coupling the hoop and the molded body. Each of the spars includes an inner end coupled to the molded body and an outer end coupled to the hoop. The inner ends of the spars are spaced from one another and held in position relative to one another by the molded body. The method includes molding the monolithic molded body from the non-metallic material, attaching inner ends of the spars to the molded body at spaced apart inner locations, and attaching outer ends of the spars to the hoop at spaced apart outer locations.

A paramotor assembly, a unibody frame for such a paramotor assembly, and a method of making a paramotor assembly are provided. The paramotor assembly includes a monolithic, non-metallic molded body, a hoop extending at least partially around the molded body, and spars coupling the hoop and the molded body. Each of the spars includes an inner end coupled to the molded body and an outer end coupled to the hoop. The inner ends of the spars are spaced from one another and held in position relative to one another by the molded body. The method includes molding the monolithic molded body from the non-metallic material, attaching inner ends of the spars to the molded body at spaced apart inner locations, and attaching outer ends of the spars to the hoop at spaced apart outer locations.

Current foot-launched 2-stroke commercial PPG offerings can meet the specified threshold (and in some cases, objective) requirements for flight ceiling, payload capacity and range with little to no modification. We will discuss those in the next section. The APES system enhances the effectiveness and lethality of the PPG-equipped unit by reducing weight of the PPG, increasing reliability and redundancy, reducing pilot workload, and seamlessly integrating with UAV's and UGV's. System improvements in the following areas is assessed: Series hybrid-electric powertrain, Coaxial propellers. Localization, autopilot, and formations, Auto landing and other advanced features, Integration with unmanned systems, and Launch Considerations.

Current foot-launched 2-stroke commercial PPG offerings can meet the specified threshold (and in some cases, objective) requirements for flight ceiling, payload capacity and range with little to no modification. We will discuss those in the next section. The APES system enhances the effectiveness and lethality of the PPG-equipped unit by reducing weight of the PPG, increasing reliability and redundancy, reducing pilot workload, and seamlessly integrating with UAV's and UGV's. System improvements in the following areas is assessed: Series hybrid-electric powertrain, Coaxial propellers. Localization, autopilot, and formations, Auto landing and other advanced features, Integration with unmanned systems, and Launch Considerations.

A variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising. in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.