Progressive 3-axis multi-variable propulsion vectoring aerial and spacecraft vehicle

A vehicle adapted for flight comprising:

• an airframe comprising a top, side, and bottom;
• at least one top exhaust port on the airframe top;
• at least one side exhaust port on the airframe side;
• at least one bottom exhaust port on the airframe bottom;
• at least one air intake located on the airframe side, the airframe side being beveled at an angle down from horizontal;
• a gas plenum in fluid communication with the exhaust ports;
• the exhaust ports each comprising, a door;
• a gas-generating means comprising:
• an air accumulator in fluid communication with the at least one air intake;
• a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;
• at least one fuel burner can in fluid communication with the compressor section;
• a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the fuel burner can, the gas plenum in fluid communication with the turbine section;
• and
• a fuel tank in fluid communication with the at least one fuel burner can.

A vehicle adapted for flight comprising:

• an airframe comprising a top, side, and bottom;
• at least one top exhaust port on the airframe top;
• at least one side exhaust port on the airframe side;
• at least one bottom exhaust port on the airframe bottom;
• the exhaust ports each comprising a door;
• a gas plenum in fluid communication with the exhaust ports;
• a gas-generating means comprising:
• a propellant tank;
• and
• at least one propellant burner can in fluid communication with the propellant tank, the at least one propellant burner can in fluid communication with the gas plenum.

A method for controlling a vehicle adapted for flight, the vehicle comprising:

• a flight control computer comprising a database of preprogrammed control parameters;
• at least one vehicle position sensor in electrical communication with the flight control computer;
• an airframe comprising:
• a top, side, and bottom;
• and
• at least one top exhaust port on the airframe top, at least one side exhaust port on the airframe side, and at least one bottom exhaust port on the airframe bottom, the exhaust ports each comprising a door;
• and
• a supply of gas distributed to the at least one top, side and bottom exhaust port, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of gas out of one or more exhaust ports, the flight control computer in electrical communication with the exhaust port doors;
• the method comprising:
• communicating a course change command to the flight control computer wherein the flight control computer chooses from the database of preprogrammed control parameters based on the course change command to affect the course change by selectively opening and closing at least one exhaust port door;
• sensing the vehicle position with the at least one position sensor;
• communicating the position data to the flight control computer;
• and
• processing the position data with the flight control computer such that the flight control computer may choose the appropriate preprogrammed control parameters to affect the course change, wherein the fight control computer and the at least one position sensor are in a continual feed-back loop.

A vehicle adapted for flight, comprising:

• an airframe comprising a top, side, and bottom;
• at least one top exhaust port on the airframe top;
• at least one side exhaust port on the airframe side;
• at least one bottom exhaust port on the airframe bottom;
• a supply of gas distributed within the airframe to the at least one top, side and bottom exhaust ports, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of gas out of at least one exhaust port;
• at least one air intake located on the airframe, the at least one air intake comprising a door;
• each exhaust port having an exhaust port door;
• an air accumulator in fluid communication with the at least one air intake;
• a gas-generating means within the airframe comprising:
• a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;
• at least one fuel burner can in fluid communication with the compressor section;
• a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the burner can;
• a gas plenum in fluid communication with the turbine section, the exhaust ports in fluid communication with the gas plenum;
• a fuel tank in fluid communication with the at least one fuel burner can;
• a propellant tank;
• at least one propellant burner can in fluid communication with the propellant tank, the at least one propellant burner can in fluid communication with the gas plenum;
• a gas plenum door between the turbine section and the gas plenum such that when closed the turbine section is substantially scaled off from the gas plenum;
• and
• an onboard flight control computer, such that the flight control computer controls the opening of the exhaust port doors.

A vehicle adapted for flight, comprising:

• an airframe comprising a plurality of exhaust ports on a top, a plurality of exhaust ports on a side, and a plurality of exhaust ports on a bottom;
• at least one of said exhaust ports on each of the airframe top, side and bottom, said exhaust ports each comprising a door adapted to be operated independently, in any combination with each other, and in any range between fully open and fully closed;
• and
• a supply of gas distributed to the exhaust ports, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of the gas out of the exhaust ports.