VTOL Aircraft Having Ducted Thrust From A Central Fan

a centrifugal fan and vtol technology, applied in the direction of vertical landing/taking-off aircraft, fuselage, transportation and packaging, etc., can solve the problems of limited flight time and payload capacity, inability to accommodate the use of fuel (e.g. gasoline), and inefficiency of the use of rotors or propellers

Inactive Publication Date: 2019-12-05
VEDAMANIKAM MARAN JOHN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The design increases lift and thrust, reduces fuel consumption and carbon emissions, and improves safety by eliminating exposed rotors, allowing for longer flight times and greater payload capacity.

Problems solved by technology

Currently-available VTOL drone aircrafts are of the multi-rotor type that suffer from limited flight time and payload capacity due to two main reasons: their electrical operation which requires heavy batteries that must be recharged over a period of time, and the inefficiency of the use of rotors or propellers that do not provide high amounts of overall lift.
They cannot accommodate the use of fuel (e.g. gasoline) for quick mission turnaround time and must use additional pre-charged batteries.
The weight of the batteries limits the amount of payload they can carry, as well as the operational flight time, because batteries do not have a high energy capacity in relation to their weight like fuel does.
The current aircraft typically have exposed rotors or propellers that create safety hazards to personnel and property.

Method used

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  • VTOL Aircraft Having Ducted Thrust From A Central Fan
  • VTOL Aircraft Having Ducted Thrust From A Central Fan
  • VTOL Aircraft Having Ducted Thrust From A Central Fan

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0014]A VTOL aircraft having thrust and directional control comprises a main body. The main body has an upper shell in a shape of a parabola, with the shape of a parabola facing and expanding into a downward-facing end. The upper shell of the main body has a top opening in a shape of a circle. The main body also has a bottom plate in a shape of a flat circle, sealed to the downward-facing end of the upper shell of the main body. The top opening of the upper shell of the main body provides an inlet for air to enter into the housing. The upper shell of the main body has at least one opening.

[0015]A fan provides a centrifugal flow of air. The fan has a central hub, and a plurality of blades extends radially outward from the central hub. The fan is mounted to the bottom plate of the main body.

[0016]At least one duct allows and directs air flow. At least one nozzle allows for exhaust release. Each nozzle is attached one each of the ducts. Each nozzle has a turn measuring 90° and facing d...

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PUM

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Abstract

A VTOL aircraft having thrust and directional control comprises a fan for providing a centrifugal flow of air. At least one duct allows for and directs air flow. At least one nozzle allows for exhaust release. Each of the at least one nozzle has a first end attached to one of each of the at least one duct. Each of the at least one nozzle has a turn measuring 90 and faces downward from the second end of each of the at least one duct. Each of the at least one nozzle has a second end at which is a vane for redirecting airflow. The VTOL aircraft also has an attachment for landing.

Description

CROSS-REFERENCES TO RELATED APPLICATIONS[0001]This application claims priority from U.S. Provisional Application Ser. No. 62 / 448,891 filed Jan. 20, 2017, which is hereby incorporated herein by reference in its entirety.FIELD OF THE INVENTION[0002]The present invention relates to a multi-ducted centrifugal fan VTOL aircraft.BACKGROUND OF THE INVENTION[0003]Currently-available VTOL drone aircrafts are of the multi-rotor type that suffer from limited flight time and payload capacity due to two main reasons: their electrical operation which requires heavy batteries that must be recharged over a period of time, and the inefficiency of the use of rotors or propellers that do not provide high amounts of overall lift. They cannot accommodate the use of fuel (e.g. gasoline) for quick mission turnaround time and must use additional pre-charged batteries. The weight of the batteries limits the amount of payload they can carry, as well as the operational flight time, because batteries do not ha...

Claims

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Application Information

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Patent Type & AuthorityApplications(United States)
IPC IPC(8): B64C29/00B64C1/06
CPCB64C39/024B64C29/0016B64C1/068B64C29/0066B64U30/20B64U20/75B64U10/20
InventorVEDAMANIKAM, MARAN JOHN
OwnerVEDAMANIKAM MARAN JOHN