Vertical Take-off and Landing Aerial Rescue and Firefighting Platform

• US 20150266570A1
• Filed: 08/12/2014
• Published: 09/24/2015
• Est. Priority Date: 01/22/2014
• Status: Active Grant

• Current Assignee: David Metreveli
• Original Assignee: David Metreveli
• Inventors: Metreveli, David
• Granted Patent: US 9,290,267 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/02 characterised by special use
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B64D 47/08 Arrangements of cameras

Abstract

A VTOL aircraft is an aerial vehicle that is utilized to reach and rescue people who are trapped in difficult-to-reach locations such as high-rise structures. The VTOL aircraft features an airframe as well as a left bidirectional thrust mechanism, and a right bidirectional thrust mechanism for providing vertical and horizontal thrust to the airframe. A plurality of engines provides torque and rotational energy that is transferred to the left bidirectional thrust mechanism and the right bidirectional thrust mechanism during operation of the VTOL aircraft. The VTOL aircraft features a housing cage on the airframe for protecting passengers, first responders, and emergency personnel onboard the aircraft. A pilot may utilize a control system located within the VTOL aircraft cockpit in order to manage the various functions of the aircraft. The VTOL aircraft features a protective enclosure for protecting the pilot from falling debris and other hazards.

Claims

1. A vertical take-off and landing (VTOL) aircraft comprises:

an airframe;

a left bidirectional thrust mechanism;

a right bidirectional thrust mechanism;

a central gearbox;

a plurality of engines;

a housing cage;

a cockpit;

a control system;

the airframe comprises a first base, a second base, and a lateral portion;

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each comprise a first ducted vertical propeller, a second ducted vertical propeller, and a ducted horizontal propeller;

the first ducted vertical propeller and the second ducted vertical propeller of the left bidirectional thrust mechanism and the first ducted vertical propeller and the second ducted vertical propeller of the right bidirectional thrust mechanism being radially positioned about the airframe;

the plurality of engines being mechanically coupled to the first ducted vertical propeller, the second ducted vertical propeller, and the ducted horizontal propeller of the left bidirectional thrust mechanism through the central gearbox;

the plurality of engines being mechanically coupled to the first ducted vertical propeller, the second ducted vertical propeller, and the ducted horizontal propeller of the right bidirectional thrust mechanism through the central gearbox;

the housing cage being mounted onto the first base;

the cockpit being centrally mounted onto the first base; and

the housing cage being positioned in between the first base and the cockpit.

2. The VTOL aircraft as claimed in claim 1 comprises:

the first ducted vertical propeller and the second ducted vertical propeller of the left bidirectional thrust mechanism being oriented normal to the second base; and

the first ducted vertical propeller and the second ducted vertical propeller of the right bidirectional thrust mechanism being oriented normal to the second base.

3. The VTOL aircraft as claimed in claim 1 comprises:

the ducted horizontal propeller of the left bidirectional thrust mechanism and the ducted horizontal propeller of the right bidirectional thrust mechanism being mounted adjacent and normal to the lateral portion; and

the ducted horizontal propeller of the left bidirectional thrust mechanism and the ducted horizontal propeller of the right bidirectional thrust mechanism being oriented parallel to each other.

4. The VTOL aircraft as claimed in claim 1 comprises:

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each further comprise a primary driveshaft, a distribution gearbox, a first secondary driveshaft, and a first output gearbox;

the central gearbox being torsionally connected into the distribution gearbox through the primary driveshaft;

the distribution gearbox being torsionally connected into the first output gearbox through the first secondary driveshaft; and

the first output gearbox being axially connected into the first ducted vertical propeller.

5. The VTOL aircraft as claimed in claim 4 comprises:

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each further comprise a first vertical opening and a first mesh protective cover;

the first vertical opening traversing through the airframe from the first base to the second base;

the first ducted vertical propeller being concentrically mounted within the first vertical opening;

the first mesh protective cover being positioned adjacent to the first ducted vertical propeller; and

the first mesh protective cover being circumferentially mounted into the airframe over the first vertical opening.

6. The VTOL aircraft as claimed in claim 1 comprises:

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each further comprise a primary driveshaft, a distribution gearbox, a second secondary driveshaft, a second output gearbox, and a tertiary driveshaft;

the central gearbox being torsionally connected into the distribution gearbox through the primary driveshaft;

the distribution gearbox being torsionally connected into the second output gearbox through the second secondary driveshaft;

the second output gearbox being axially connected into the second ducted vertical propeller; and

the second output gearbox being torsionally connected into the ducted horizontal propeller through the tertiary driveshaft.

7. The VTOL aircraft as claimed in claim 6 comprises:

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each further comprise a second vertical opening and a second mesh protective cover;

the second vertical opening traversing through the airframe from the first base to the second base;

the second ducted vertical propeller being concentrically mounted within the second vertical opening;

the second mesh protective cover being positioned adjacent to the second ducted vertical propeller; and

the second mesh protective cover being circumferentially mounted into the airframe over the second vertical opening.

8. The VTOL aircraft as claimed in claim 1 further comprises:

a plurality of landing wheel fixtures; and

the plurality of landing wheel fixtures being perimetrically mounted about the second base.

9. The VTOL aircraft as claimed in claim 1 further comprises:

the housing cage comprises a cage opening and a gate;

the housing cage being positioned in between the first ducted vertical propeller and the second ducted vertical propeller for both the left bidirectional thrust mechanism and the right bidirectional thrust mechanism;

the cage opening being positioned in between the first ducted vertical propeller of the left bidirectional thrust mechanism and the first ducted vertical propeller of the right bidirectional thrust mechanism;

the gate being hingedly mounted to the first base; and

the gate being positioned adjacent to the cage opening, wherein the gate is used to selectively cover the cage opening.

10. The VTOL aircraft as claimed in claim 1 further comprises:

an extendable walkway;

the extendable walkway being positioned adjacent to a cage opening of the housing cage; and

the extendable walkway being laterally mounted to the airframe.

11. The VTOL aircraft as claimed in claim 1 further comprises:

a ladder;

the ladder being positioned adjacent to a cage opening of the housing cage; and

the ladder being laterally and hingedly mounted to the airframe.

12. The VTOL aircraft as claimed in claim 1 further comprises:

the control system being electronically connected to the plurality of engines;

13. The VTOL aircraft as claimed in claim 1 further comprises:

the cockpit comprises a foundation, an access hatch, and a protective enclosure;

the protective enclosure being centrally mounted on the first base by the foundation;

the access hatch traversing from the housing cage into the protective enclosure; and

the control system being positioned within the protective enclosure.

14. The VTOL aircraft as claimed in claim 1 further comprises:

a camera system;

the camera system being pivotally mounted to the second base;

the camera system being positioned adjacent to the lateral portion; and

the camera system being electronically connected to the control system.

15. The VTOL aircraft as claimed in claim 1 further comprises:

a plurality of impact sensor cables;

the plurality of impact sensor cables being perimetrically mounted about the second base; and

the plurality of impact sensor cables being electronically connected to the control system.

16. The VTOL aircraft as claimed in claim 1 further comprises:

a hoist;

the hoist being swivelably mounted on the first base; and

the hoist being electronically connected to the control system.

17. A VTOL aircraft comprises:

an airframe;

a left bidirectional thrust mechanism;

a right bidirectional thrust mechanism;

a central gearbox;

a plurality of engines;

a housing cage;

a cockpit;

a control system;

a plurality of landing wheel fixtures;

an extendable walkway;

a ladder;

a camera system;

a plurality of impact sensor cables;

a hoist;

the airframe comprises a first base, a second base, and a lateral portion;

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each comprise a first ducted vertical propeller, a second ducted vertical propeller, and a ducted horizontal propeller;

the first ducted vertical propeller and the second ducted vertical propeller of the left bidirectional thrust mechanism and the first ducted vertical propeller and the second ducted vertical propeller of the right bidirectional thrust mechanism being radially positioned about the airframe;

the plurality of engines being mechanically coupled to the first ducted vertical propeller, the second ducted vertical propeller, and the ducted horizontal propeller of the left bidirectional thrust mechanism through the central gearbox;

the plurality of engines being mechanically coupled to the first ducted vertical propeller, the second ducted vertical propeller, and the ducted horizontal propeller of the right bidirectional thrust mechanism through the central gearbox;

the housing cage comprises a cage opening and a gate;

the housing cage being mounted onto the first base;

the cockpit comprises a foundation, an access hatch, and a protective enclosure;

the cockpit being centrally mounted onto the first base;

the protective enclosure being centrally mounted on the first base by the foundation;

the access hatch traversing from the housing cage into the protective enclosure;

the control system being positioned within the protective enclosure;

the control system being electronically connected to the plurality of engines;

the housing cage being positioned in between the first base and the cockpit.

the plurality of landing wheel fixtures being perimetrically mounted about the second base.

the extendable walkway being positioned adjacent to the cage opening;

the extendable walkway being laterally mounted to the airframe.

the ladder being positioned adjacent to the cage opening;

the ladder being laterally and hingedly mounted to the airframe.

the camera system being pivotally mounted to the second base;

the camera system being positioned adjacent to the lateral portion;

the camera system being electronically connected to the control system;

the plurality of impact sensor cables being perimetrically mounted about the second base; and

the plurality of impact sensor cables being electronically connected to the control system.

the hoist being swivelably mounted on the first base;

the hoist being electronically connected to the control system;

18. The VTOL aircraft as claimed in claim 17 further comprises:

the first ducted vertical propeller and the second ducted vertical propeller of the left bidirectional thrust mechanism being oriented normal to the second base;

the first ducted vertical propeller and the second ducted vertical propeller of the right bidirectional thrust mechanism being oriented normal to the second base;

the ducted horizontal propeller of the left bidirectional thrust mechanism and the ducted horizontal propeller of the right bidirectional thrust mechanism being mounted adjacent and normal to the lateral portion; and

the ducted horizontal propeller of the left bidirectional thrust mechanism and the ducted horizontal propeller of the right bidirectional thrust mechanism being oriented parallel to each other.

19. The VTOL aircraft as claimed in claim 17 further comprises:

the left bidirectional thrust mechanism and the right bidirectional thrust mechanism each further comprise a primary driveshaft, a distribution gearbox, a first secondary driveshaft, a first output gearbox, a tertiary driveshaft, a first vertical opening, a first mesh protective cover, a second secondary driveshaft, a second output gearbox, a second vertical opening, and a second mesh protective cover;

the central gearbox being torsionally connected into the distribution gearbox through the primary driveshaft;

the distribution gearbox being torsionally connected into the first output gearbox through the first secondary driveshaft;

the first output gearbox being axially connected into the first ducted vertical propeller;

the first vertical opening traversing through the airframe from the first base to the second base;

the first ducted vertical propeller being concentrically mounted within the first vertical opening;

the first mesh protective cover being positioned adjacent to the first ducted vertical propeller;

the first mesh protective cover being circumferentially mounted into the airframe over the first vertical opening;

the central gearbox being torsionally connected into the distribution gearbox through the primary driveshaft;

the distribution gearbox being torsionally connected into the second output gearbox through the second secondary driveshaft;

the second output gearbox being axially connected into the second ducted vertical propeller;

the second output gearbox being torsionally connected into the ducted horizontal propeller through the tertiary driveshaft;

the second vertical opening traversing through the airframe from the first base to the second base;

the second ducted vertical propeller being concentrically mounted within the second vertical opening;

the second mesh protective cover being positioned adjacent to the second ducted vertical propeller; and

the second mesh protective cover being circumferentially mounted into the airframe over the second vertical opening.

20. The VTOL aircraft as claimed in claim 17 further comprises:

the housing cage being positioned in between the first ducted vertical propeller and the second ducted vertical propeller for both the left bidirectional thrust mechanism and the right bidirectional thrust mechanism;

the cage opening being positioned in between the first ducted vertical propeller of the left bidirectional thrust mechanism and the first ducted vertical propeller of the right bidirectional thrust mechanism;

the gate being hingedly mounted to the first base; and

the gate being positioned adjacent to the cage opening, wherein the gate is used to selectively cover the cage opening.