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A quadcopter is a Vertical Takeoff and Landing (VTOL) aerial vehicle consisting of a fuselage surrounded by four independent, vertical axis propulsory. By varying the distribution of speed and power to the propulsion modules, forward controlled flight is possible. The quadcopter propulsion modules continuously provide the thrust to both lift the craft and then generate forward motion. The propulsion modules may or may not have the capability to tilt in the fore and aft direction. For the quadcopter with propulsion modules that tilt, more thrust is available for forward motion with an adjustable flight trim.
The typical quadcopter design consists of a fuselage designed to reduce drag but not to provide significant lift. Because all of the lift is provided by the propulsion, the energy expended to offset the vehicle weight reduces the available energy for flight range and duration. The fuselage provides limited space for equipment and there is poor access to the interior volume for loading of passengers or cargo due to the surrounding propulsion system. Many versions, from small to large size, are limited to carrying payload appended to the exterior of the fuselage. The appended payload is less desirable than having the access and volume to carrying it partially or fully within the fuselage since the payload is unprotected from the elements and adds aerodynamic drag.
The propulsion modules typically make up the four outer corners of the vehicle and have swept diameters outside the footprint of the fuselage in order to minimize slipstream interaction. This arrangement substantially reduces the available footprint for the fuselage for a given overall length and width.
Lastly, state-of-the-art quadcopters typically have fixed strut landing gear without wheels thus limiting the aerial vehicle to only a vertical takeoff and landing (VTOL) mode. Some versions have folding struts for a more compact stowage arrangement or to reduce aerodynamic drag in flight; however, wheels are typically not utilized for ground mobility or short takeoff and landing (STOL) capabilities.
A novel diamond quadcopter 10 is described that provides improvements in flight performance and payload utility. Said diamond quadcopter 10, illustrated in
Inherent to a quadcopter, said propulsive modules 30 are controlled by computers to provide flight attitude control and VTOL operation. As illustrated in
As illustrated in
Said forward propulsion module support foils 50 and said aft propulsion module support foils 60 may have, in an embodiment, internally mounted landing struts 90 illustrated in
Said landing struts 90 have a caster nose wheel 100 mounted on one pair and have main landing wheels 110 mounted on a second pair. In an embodiment, said main landing wheel 110 may incorporate hub motors 120 for ground maneuvering. Collective or differential powering of said hub motor 120 in combination with said caster nose wheel 100 allows maneuverability on the ground without the use of said propulsion modules 30. Said hub motor 120 may also assist with power during short takeoff and with regenerative braking during a rolling landing.
Said propulsive modules 30 are tilted by said rotary actuators 40 to transition from vertical thrust for take-off and landing mode to a more horizontal thrust during flight mode, as illustrated in
In a second embodiment illustrated in
With said landing struts 90 fully retracted the thin, flat shape of said cross structure 70 allows said hinge 140 to be in close proximity to the ground. The low height of said hinge 140 allows a very shallow angle for said ramp 130 for easy walk-on or roll-on of payload, for example passengers using wheelchairs or gurneys, and without the inconvenience of having to climb into a fuselage.
In a third embodiment illustrated in
Utilizing said hub motor 120 or said propulsion module 30, said diamond quadcopter 10 maneuvers over and lowers onto a cargo package through said bottom door 150 using the extension and retraction of said landing struts 90. With no cargo package loaded, or with it released and jettisoned during flight, said bottom door 150 opening may be utilized in manned flights as an emergency egress exit.
In a fourth embodiment illustrated in
Said rotary actuators 40 control movement of said power modules 30 and said forward cross foil 160 and said aft cross foil 170. Solid spans are illustrated in
Summary
This patent describes a diamond quadcopter with a diamond faceted fuselage that generates forward flight lift while providing open corner regions for foil supported propulsion modules that minimize propulsion module slipstream interaction with the fuselage in the different modes of operation. The geometry is scaleable in various embodiments from small size vehicles carrying instruments to mid-sized vehicles carrying packages to large size vehicles carrying cargo and/or people.
Internal to the propulsion module support foils are vertically extendable landing struts with mounted wheels that allow rolling and non-rolling take-offs and landings and provide for maneuverability and control of the height and attitude of the diamond quadcopter while on the ground.
The diamond faceted fuselage has a flat bottom facet allowing the vehicle in one embodiment to settle close to the ground thereby allowing access to the interior via a shallow angled ramp swung open from the lower edge of the aft facet.
The flat bottom facet also allows an embodiment to provides access to the fuselage interior through a bottom door; thereby, allowing the quadcopter to maneuver over and settle onto cargo utilizing height adjustment of the landing struts.
The modes of operation include vertical take-off and landing, conventional short take-off and landing and emergency landings, tilting propulsion during flight, and ground loading and unloading of payload via bottom insertion or via ramp.
This application claims the benefit of provisional patent application 62/561,682 filed 2017, Sep. 22 by the present inventor.
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Number | Date | Country | |
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20190092445 A1 | Mar 2019 | US |
Number | Date | Country | |
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62561682 | Sep 2017 | US |