Gyroscopically stabilised firefighting aerial vehicles

An aerial vehicle comprising:

• an aerodynamic body;
• one or more jet turbines and/or electric motors and/or engines coupled to an aerial vehicle frame and/or fuselage of the aircraft body to provide thrust and/or power to the aerial vehicle;
• and
• wherein the one or more jet turbines and/or motors and/or engines may rotate 360 degrees in any direction;
• and
• wherein a central hub drive assembly and/or a radial distal fan blade drive assembly is configured to be driven by the one or more jet turbines and/or electric motors and/or engines and/or power allowing the pivot of the fan blades and rotation of a gyroscopic fan blade assembly;
• and
• wherein the one or more fan blades of the gyroscopic fan blade assembly may be variable, and provide pitch reversal, changing the thrust direction;
• the one or more gyroscopic stabilisation assembly comprising at least one gyroscopic member are powered by the one or more jet turbines and/or electric motors and/or engines and/or power systems to gyroscopically stabilise the aerial vehicle during flight;
• and
• and/or an attached cabin and/or cockpit module and/or a pivotally attached cabin and/or cockpit module attached to the aerial vehicle frame and/or fuselage, and/or cabin is a movably coupled cabin and/or cockpit module, and/or is detached from the aerial vehicle frame and/or fuselage and/or cabin for autonomous flight;
• and
• wherein the pivotally attached cabin and or cockpit module may be attached to and pivot with a pivotally attached articulated wing, providing pitch to the aerial vehicle and roll of the cabin and or cockpit module;
• and
• wherein the cabin and/or cockpit module is gimballed, allowing 360-degree rotation in any direction, providing a stabilised flight characteristic;
• and
• wherein the shape of an aerial vehicle frame and/or fuselage and/or cabin and/or cockpit may be in the form of a torus;
• and
• wherein the one or more jet turbines and/or electric motors and/or engines are mounted to the inner of the outer surfaces of the aerial vehicle frame and/or fuselage and/or cabin;
• and
• wherein the aerial vehicle has a plurality of control surfaces;
• and
• wherein the one or more aerial vehicles may be attached to one or more aircraft;
• and
• wherein the aerial vehicles may take off and land on a water base and or a land base;
• and
• wherein the aerial vehicle is adapted to direct thrust from the one or more jet turbines and/or electric motors and/or engines during hovering take off and landing and firefighting, the jet turbines and/or electric motors and/or engines are in the vertical orientation relative to the horizon, providing thrust to the aerial vehicle and direct thrust in a desirable direction for suppressing a fire;
• and
• wherein the aerial vehicle is configured to direct thrust from one or more jet turbines, electric motors, or engines in a horizontal direction during flight, the jet turbines, electric motors, or engines being oriented horizontally relative to the horizon, thereby providing thrust to the aerial vehicle to facilitate forward motion in a desired direction.