Modular aircraft system

• US 9,505,484 B1
• Filed: 04/11/2016
• Issued: 11/29/2016
• Est. Priority Date: 04/11/2016
• Status: Active Grant

• Current Assignee: Nasser M. Al-Sabah
• Original Assignee: Nasser M. Al-Sabah
• Inventors: Al-Sabah, Nasser M.
• Primary Examiner(s): BENEDIK, JUSTIN M
• Application Number:
  US15/096,216
• Time in Patent Office: 232 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/00 Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
• CPC Class Codes: B64C 13/20 using radiated signals
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• CPC Class Codes: B64C 3/34 Tanks constructed integrally with wings, e.g. for fuel or water
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: B64C 5/06 Fins B64C5/08 takes precedence
• CPC Class Codes: B64C 9/00 Adjustable control surfaces or members, e.g. rudders trimming stabilising surfaces B64C5/10
• CPC Class Codes: B64C 9/326 associated with fuselages
• CPC Class Codes: B64D 15/00 De-icing or preventing icing on exterior surfaces of aircraft motor vehicles specially adapted for carrying de-icing equipment B60P
• CPC Class Codes: B64D 27/02 Aircraft characterised by the type or position of power plants fuselages specially adapted for mounting power plants B64C1/16; wings specially adapted for power plants B64C3/32
• CPC Class Codes: B64D 27/14 within, or attached to, fuselages
• CPC Class Codes: B64D 27/20 within, or attached to, fuselages
• CPC Class Codes: B64D 37/00 Arrangements in connection with fuel supply for power plant refuelling during flight B64D39/00
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 2101/00 UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/10 : Wings
• CPC Class Codes: B64U 30/14 : detachable
• CPC Class Codes: B64U 30/40 : Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 50/00 : Propulsion; Power supply
• CPC Class Codes: B64U 50/12 : using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 : using external fans or propellers
• CPC Class Codes: B64U 50/14 : ducted or shrouded
• CPC Class Codes: B64U 50/34 : In-flight charging photovoltaics B64U50/31
• CPC Class Codes: Y02T 50/30 : Wing lift efficiency

Abstract

The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.

Claims

1. A modular aircraft system, comprising:

a fuselage having an empennage and rearwardly disposed first and second engine module stations, the empennage being permanently affixed to the fuselage;

a plurality of mutually interchangeable wing modules, each of the wing modules being adapted for detachable connection to the fuselage, each of the wing modules comprising a left wing and a right wing, the wing modules having identical wing root configurations to one another and different spans and aspect ratios from one another;

a plurality of mutually interchangeable engine modules, each engine module being different from another engine module and being adapted for detachable connection to engine module stations of the fuselage;

an on-board fuel supply;

a fuel delivery line deployed from the fuselage; and

a fuel delivery system and wherein the fuel delivery line and the fuel delivery system are adapted for airborne delivery of fuel from the on-board fuel supply to another aircraft.

2. The modular aircraft system according to claim 1, wherein the modular aircraft is an unmanned aerial vehicle, and the fuselage comprises a selectively deployable aerodynamic brake disposed thereon, the aerodynamic brake being in front of the engine module stations.

3. The modular aircraft system according to claim 1, wherein:

the fuselage comprises left and right wing root attachment stations, the wing root attachment stations being in mirror image to one another;

each of the wing root attachment stations includes at least one of mechanical fittings electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

the left wing and the right wing of each of the wing modules includes wing root configurations in mirror image to one another, each of the wing root configurations being adapted for removable attachment to a corresponding one of the wing root attachment stations of the fuselage;

each of the wing root configurations includes at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

the engine module stations of the fuselage includes at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings; and

each of the engine modules includes an attachment base, each attachment base includes at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings, each of the engine modules being adapted for removable attachment to the engine module stations of the fuselage.

4. The modular aircraft system according to claim 1, wherein the empennage includes a fixed stabilizer and movable elevators, the stabilizer having left and right outboard tips, each of the tips having fixed upward and downward fins extending therefrom, each of the upward fins having a movable rudder.

5. The modular aircraft system according to claim 1, wherein the plurality of engine modules include a first engine module, a second engine module, and a third engine module, the first engine module being a single turboprop, the second engine module being a single turbojet, and the third engine module being dual turbojets.

6. The modular aircraft system according to claim 1, further comprising at least one payload bay disposed within the fuselage.

7. The modular aircraft system according to claim 1,

wherein the fuel supply comprising at least one of an internal fuselage tank, an internal wing tank, and an external wing tank.

8. An unmanned aerial vehicle system, comprising:

a fuselage, the fuselage having an empennage permanently affixed thereto;

wherein the empennage includes a fixed stabilizer and movable elevators, the stabilizer having left and right outboard tips, each of the tips having fixed upward and downward fins extending therefrom, each of the upward fins having a movable rudder;

a plurality of mutually interchangeable engine modules, each of the engine modules being adapted for individual installation upon the fuselage, the engine modules comprising a first engine module, a second engine module, and a third engine module, the first engine module including a single turboprop, the second engine module including a single turbojet, and the third engine module including dual turbojets;

rearwardly disposed first and second engine module stations on the fuselage; and

a plurality of mutually interchangeable engine modules, each engine module being different from another engine module and being adapted for detachable connection to engine module stations of the fuselage;

a plurality of mutually interchangeable wing modules, each of the wing modules being adapted for detachable connection to the fuselage, each of the wing modules comprising a left wing and a right wing, the wing modules having identical wing root configurations to one another and different spans and aspect ratios from one another;

a selectively deployable aerodynamic brake disposed atop the fuselage and in front of the engine module;

an on-board fuel supply;

a fuel delivery line deployed from the fuselage; and

a fuel delivery system, the fuel delivery line and the fuel delivery system being adapted for the airborne delivery of fuel from the on-board fuel supply to another aircraft; and

at least one payload bay disposed within the fuselage.

9. The unmanned aerial vehicle system according to claim 8, further comprising:

left and right wing root attachment stations on the fuselage, the left and right wing root attachment stations being in mirror image to one another, each wing root attachment station of the fuselage including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings; and

wing root configurations on the left wing and the right wing of each of the wing modules, the wing root configurations of the left wing and the right wing of each of the wing modules being in mirror image to one another, each of the wing root configurations being adapted for attachment to a corresponding one of the wing root attachment stations of the fuselage, each of the wing root configurations including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

rearwardly disposed first and second engine module stations on the fuselage, the engine module stations including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings; and

a plurality of engine modules, each of the engine modules having an attachment base, each attachment base including at least one of a plurality of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings adapted for removable attachment to the engine module stations of the fuselage.

10. A modular aircraft system, comprising:

a fuselage having an empennage permanently affixed thereto and left and right wing root attachment stations, the wing root attachment stations being in mirror image to one another, each wing root attachment station of the fuselage including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

wherein the empennage includes a fixed stabilizer and movable elevators, the stabilizer having left and right outboard tips, each of the tips having fixed upward and downward fins extending therefrom, and each of the upward fins having a movable rudder;

a plurality of wing modules, each of the wing modules including a left wing and a right wing, the left wing and the right wing of each of the wing modules having mirror image wing root configurations to one another, each of the wing root configurations being adapted for selective detachable connection to a corresponding one of the wing root attachment stations of the fuselage, and each of the wing root configurations including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

the fuselage further having rearwardly disposed first and second engine module stations, the engine module stations including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

a plurality of engine modules, the engine modules and the engine module stations of the fuselage being adapted for detachable connection to the engine module stations of the fuselage, each of the engine modules having an attachment base, each attachment base including at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, and fuel supply fittings;

an on-board fuel supply, the fuel supply including at least one of internal fuselage tanks, internal wing tanks, and external wing tanks;

a fuel delivery line deployed from the fuselage; and

a fuel delivery system, the fuel delivery line and the fuel delivery system being adapted for airborne delivery of fuel from the on-board fuel supply to another aircraft.

11. The modular aircraft system according to claim 10, wherein:

the wing modules have identical wing root configurations to one another and different spans and aspect ratios from one another; and

each engine module is different.

12. The modular aircraft system according to claim 10, wherein:

the modular aircraft is an unmanned aerial vehicle; and

the fuselage includes one payload bay and a selectively deployable aerodynamic brake, the aerodynamic brake being on the fuselage and in front of the engine module stations.

13. The modular aircraft system according to claim 10, wherein the engine modules comprise a single turboprop, a single turbojet and dual turbojets.