Geometry optimized low aspect ratio vtol vehicle system with structurally integrated propulsion

A self-contained vertical takeoff and landing vehicle (VTOL) system comprising:

• a skin 183 and fuel tanks 182 lining an inside of said skin and integrated therewith to form a unitary structural skeleton 120 that has a rounded outer surface;
• wherein the fuel tanks comprise internal lattice structures formed of one or more groups of multiplicities of interconnected cells 1310 lining and integrated with an inside of said skin over a sufficient area thereof to enhance structural strength of said structural skeleton and to reduce fuel slosh compared with tanks lacking such lattice structures;
• a rocket propulsion system 180 that has aft-facing exhaust nozzles 350 at a periphery of an aft portion of said structural skeleton and is coupled with one or more of said fuel tanks for supply of rocket fuel;
• and
• an airbreathing propulsion system 170 that has aft facing exhaust nozzles 362 radially inwardly spaced from said rocket propulsion system exhaust nozzles and is coupled with one of more said fuel tanks for supply of fuel for airbreathing propulsion;
• wherein said rocket and airbreathing propulsion systems are configured to operate selectively to provide sufficient propulsion for ascent, descent, and landing of said VTOL system.

A self-contained vertical takeoff and landing vehicle (VTOL) system comprising:

• a skin 183 and fuel tanks 182 lining an inside of said skin and integrated therewith to form a unitary structural skeleton 120 that has a rounded outer surface and an aspect ratio of height to maximum width no greater than 5.3:1;
• a rocket propulsion system 180 that has aft-facing exhaust nozzles 350 at a periphery of an aft portion of said structural skeleton and is coupled with one or more of said fuel tanks for supply of rocket fuel;
• and
• an airbreathing propulsion system 170 that has aft facing exhaust nozzles 362 radially inwardly spaced from said rocket propulsion system exhaust nozzles and is coupled with one of more said fuel tanks for supply of fuel for airbreathing propulsion;
• wherein said rocket and airbreathing propulsion systems are configured to operate selectively to provide sufficient propulsion for ascent, descent, and landing of said VTOL system.

A self-contained vertical takeoff and landing vehicle (VTOL) system comprising:

• a skin 183 and fuel tanks 182 lining an inside of said skin and integrated therewith to form a unitary structural skeleton 120 that has a rounded outer surface and an aspect ratio of height to maximum width no greater than 5.3:1;
• wherein the fuel tanks comprise internal lattice structures formed of one or more groups of multiplicities of interconnected cells 1310 lining and integrated with an inside of said skin over a sufficient area thereof to enhance structural strength of said structural skeleton and to reduce fuel slosh compared with tanks lacking such lattice structures;
• and
• a propulsion system [170 and/or 180] that has at least 10 aft-facing exhaust nozzles [350 and/or 362] arranged in a ring at an aft portion of said structural skeleton and is coupled with one or more of said fuel tanks for supply of fuel;
• wherein said propulsion systems is configured to operate selectively to provide sufficient propulsion for ascent, descent, and landing of said VTOL system.

A process of vertical takeoff and landing (VTOL) comprising:

• forming a structural skeleton 120 that has a rounded outer surface and an aspect ratio of height to maximum width no greater than 5.3:1 by lining an inside of a skin 183 with fuel tanks 182 integrated therewith;
• wherein said lining the skin with fuel tanks comprises forming the fuel tanks with internal lattice structures of one or more groups of multiplicities of interconnected cells 1310 lining and integrated with the inside of said skin over a sufficient area thereof to enhance structural strength of said structural skeleton and to reduce fuel slosh compared with tanks lacking such lattice structures;
• securing to said structural skeleton a rocket propulsion system 180 that has aft-facing exhaust nozzles 350 at a periphery of an aft portion of said structural skeleton and is coupled with one or more of said fuel tanks for supply of rocket fuel;
• further securing to said structural skeleton an airbreathing propulsion system 170 that has aft facing exhaust nozzles 362 radially inwardly spaced from said rocket propulsion system exhaust nozzles and is coupled with one of more said fuel tanks for supply of fuel for airbreathing propulsion;
• and
• configuring said rocket and airbreathing propulsion systems to operate selectively to provide sufficient propulsion for ascent, descent, and landing of said VTOL vehicle.