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NZ786029B2 - Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities - Google Patents
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NZ786029B2 - Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities - Google Patents

Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities

Info

Publication number
NZ786029B2
NZ786029B2 NZ786029A NZ78602920A NZ786029B2 NZ 786029 B2 NZ786029 B2 NZ 786029B2 NZ 786029 A NZ786029 A NZ 786029A NZ 78602920 A NZ78602920 A NZ 78602920A NZ 786029 B2 NZ786029 B2 NZ 786029B2
Authority
NZ
New Zealand
Prior art keywords
aircraft
aerial vehicle
wing
fixed
constructed
Prior art date
Application number
NZ786029A
Other versions
NZ786029A (en
Inventor
Matthew T Velazquez
Original Assignee
Textron Systems Corporation
Filing date
Publication date
Priority claimed from US16/599,454 external-priority patent/US11542004B2/en
Application filed by Textron Systems Corporation filed Critical Textron Systems Corporation
Publication of NZ786029A publication Critical patent/NZ786029A/en
Publication of NZ786029B2 publication Critical patent/NZ786029B2/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
    • B64D1/10—Stowage arrangements for the devices in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/30—Launching, take-off or landing arrangements for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
    • G01S13/933—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/88—Lidar systems specially adapted for specific applications
    • G01S17/93—Lidar systems specially adapted for specific applications for anti-collision purposes
    • G01S17/933—Lidar systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/14—Receivers specially adapted for specific applications
    • G01S19/15—Aircraft landing systems

Abstract

aerial vehicle 24 that provides vertical takeoff and landing (VTOL) capabilities to an aircraft 22, comprising a frame coupled to an aircraft interface. The interface is constructed and arranged to physically interface with the external aircraft. A set of rotor assemblies with a set of wing surfaces are coupled with the frame. The wing surfaces provide lift when the set of rotors provides thrust in a horizontal direction. A controller is supported by the frame, where the controller is constructed and arranged to operate the set of rotor assemblies to provide the VTOL capabilities while the aircraft interface physically interfaces with the aircraft. A scissor linkage-style hold/release assembly having a set of engaging mechanisms of the aircraft interface is constructed and arranged to extend from the set of wing surfaces to engage with an underside of the aircraft while the aerial vehicle and the aircraft fly a predefined distance apart from each other during horizontal flight. Claims are also made to the aircraft, and the multivehicle system comprising the aircraft and the aerial vehicle. The fixed-wing aircraft remains free from bulky VTOL components, enhancing airspeed, ceiling, payload capacity, and endurance, and the system enables launching and retrieving fixed-wing aircraft from limited space or unprepared surfaces.

Claims (21)

1. An aerial vehicle that provides al takeoff and landing (VTOL) capabilities to an aircraft, the aerial vehicle comprising: a frame; an aircraft interface coupled with the frame, the aircraft interface being constructed and arranged to physically interface with the aircraft which is external to the aerial vehicle; a set of rotor assemblies coupled with the frame; a set of wing surfaces that provides lift when the set of rotors provides thrust in a horizontal direction; and a controller supported by the frame, the controller being constructed and arranged to operate the set of rotor assemblies to provide the VTOL capabilities while the aircraft interface physically aces with the aircraft; n a scissor linkage-style hold/release assembly having a set of engaging mechanisms of the aircraft interface is constructed and arranged to extend from the set of wing surfaces to engage with an underside of the aircraft while the aerial vehicle and the aircraft fly a predefined ce apart from each other during horizontal flight.
2. An aerial vehicle as in claim 1 n the hold/release assembly which is mounted to the frame, the set of engaging mechanisms of the hold/release assembly being responsive to a set of hold/release signals from the controller to selectively hold the ft to the frame and release the aircraft from the frame while the aerial vehicle is in flight.
3. An aerial vehicle as in claim 2 wherein the set of engaging mechanisms of the hold/release assembly includes: a set of omagnets coupled with the frame, the set of electromagnets being constructed and arranged to control tion of the aircraft to the frame in response to the set of elease signals from the controller.
4. An aerial vehicle as in claim 2 or claim 3 wherein the set of engaging mechanisms of the hold/release assembly includes: a set of suction devices coupled with the frame, the set of suction devices being constructed and arranged to control drawing of the aircraft to the frame in response to the set of hold/release signals from the controller.
5. An aerial vehicle as in any of claims 2 through 4 wherein the set of engaging mechanisms of the hold/release assembly includes: a set of latching mechanisms coupled with the frame, the set of latching mechanisms being constructed and arranged to control fastening of the aircraft to the frame in response to the set of hold/release s from the controller.
6. An aerial vehicle as in any of claims 1 through 5, further comprising: a g assembly which is supported by the frame, the sensing assembly being constructed and arranged to provide a set of position signals to the controller to identify a position of the aircraft relative to the aerial vehicle while the aircraft and the aerial vehicle are in flight.
7. An aerial vehicle as in claim 6 wherein the sensing assembly includes: a farfield sensing subsystem constructed and ed to provide a set of farfield sensing signals to the controller, the set of farfield g s including location data that s the controller to establish ion flight between the aircraft and the aerial vehicle in response to the set of farfield sensing signals.
8. An aerial vehicle as in claim 7 wherein the g assembly further includes: a nearfield sensing subsystem constructed and arranged to e a set of nearfield sensing signals to the controller, the set of nearfield sensing signals including relative position and velocity data that enables the controller to establish soft capture proximity between the aircraft and the aerial vehicle in se to the set of nearfield sensing signals.
9. An aerial vehicle as in claim 8 wherein the nearfield sensing tem includes: a light detection and ranging (LIDAR) subsystem constructed and arranged to provide a set of LIDAR subsystem signals to the controller to identify current position and velocity of the aircraft relative to the aerial vehicle while the aircraft and the aerial vehicle are in flight.
10. An aerial vehicle as in claim 8 or claim 9 wherein the nearfield sensing subsystem includes: a radio detection and ranging (RADAR) subsystem constructed and arranged to provide a set of RADAR subsystem signals to the controller to identify current position and velocity of the aircraft relative to the aerial vehicle while the aircraft and the aerial vehicle are in flight.
11. An aerial vehicle as in any of claims 8 through 10 wherein the eld g subsystem includes: a set of optical sensors constructed and ed to provide a set of image signals to the controller to fy current position of the aircraft relative to the aerial vehicle while the aircraft and the aerial e are in .
12. An aerial vehicle as in any of claims 1 through 11 wherein the frame is constructed and arranged to carry, as the aircraft, a fixed-wing unmanned aerial vehicle (UAV) having a wing-span of at least 20 feet and an initial weight of at least 400 pounds during a vertical f maneuver.
13. An aerial vehicle as in claim 12 wherein the set of rotor assemblies is constructed and arranged to fly the aerial vehicle at a horizontal speed of at least 50 miles per hour while the aerial e carries the fixed-wing ed UAV during a release-in-flight maneuver.
14. An aerial vehicle as in claim 12 or claim 13 wherein the set of rotor assemblies includes at least four rotor assemblies, each rotor assembly being constructed and arranged to provide at least 100 pounds of lift to during the vertical f maneuver.
15. A method of operating an aerial e, comprising: capturing a wing aircraft while the aerial vehicle and the fixed-wing aircraft are concurrently in horizontal flight, the aerial vehicle including a set of rotors and a set of wing surfaces that provides lift when the set of rotors provides thrust in a horizontal direction; while the fixed-wing aircraft remains captured by the aerial vehicle, transitioning from ntal flight to hovering flight; and after transitioning from horizontal flight to ng flight, performing a vertical landing maneuver to land the aerial vehicle while the fixed-wing aircraft remains captured by the aerial vehicle; wherein capturing the wing aircraft includes extending a scissor linkage-style hold/release ly having a set of engaging mechanisms of the aerial vehicle from the set of wing surfaces of the aerial vehicle to engage with an ide of the fixed wing aircraft while the aerial vehicle and the fixed wing aircraft fly a predefined distance apart from each other during horizontal flight.
16. A method as in claim 15, further comprising: performing a vertical takeoff maneuver in which the aerial vehicle carries the fixed-wing aircraft while achieving vertical flight; tioning from vertical flight to horizontal flight while the aerial vehicle ues carrying the fixed-wing aircraft; and releasing the fixed-wing aircraft while in horizontal flight to enable the fixedwing aircraft to fly horizontally upon release.
17. A fixed-wing aircraft, comprising: a fixed-wing structure constructed and arranged to carry a payload; an aircraft propulsion system coupled with the fixed-wing structure; and an engagement section coupled with the fixed-wing structure, the engagement section being constructed and arranged to engage with an aerial vehicle while the fixed-wing aircraft is propelled by the aircraft sion system during flight, the aerial vehicle ing a set of rotors and a set of wing surfaces that, in combination with the fixed wing structure, provides lift when the set of rotors provides thrust in a horizontal direction; n the engagement section is disposed on an underside of the fixed-wing aircraft to engage a scissor linkage-style elease assembly having a set of engaging isms of the aerial vehicle when the scissor e-style hold/release assembly extends from the set of wing surfaces to engage with the underside of the aircraft while the aerial vehicle and the aircraft fly a predefined distance apart from each other during horizontal flight.
18. A method of operating a fixed-wing aircraft, comprising: flying horizontally in an independent manner while carrying a payload; after flying horizontally in the independent manner, establishing formation flight with an aerial vehicle, the aerial vehicle including a set of rotors and a set of wing surfaces that, in combination with a fixed-wing structure of the fixed-wing aircraft, provides lift when the set of rotors provides thrust in a horizontal ion; and while in formation flight with the aerial e, engaging with the aerial vehicle to enable the aerial vehicle to carry the fixed-wing aircraft and land vertically while carrying the fixed-wing aircraft; wherein engaging with the aerial vehicle includes an underside of the wing aircraft engaging a scissor linkage-style hold/release assembly having a set of ng mechanisms of the aerial vehicle when the scissor linkage-style hold/release assembly extends from the set of wing surfaces to engage with the ide of the aircraft while the aerial vehicle and the aircraft fly a predefined distance apart from each other during horizontal flight.
19. A method as in claim 18, further comprising: prior to flying horizontally in the independent , taking off vertically while being carried by the aerial e; after taking off vertically, transitioning from vertical flight to horizontal flight while being carried by the aerial vehicle; and detaching from the aerial vehicle while in horizontal flight to achieve independent horizontal flight.
20. A multivehicle system, sing: a fixed-wing aircraft and an aerial vehicle which is separate from the fixed-wing aircraft; the fixed-wing ft including: a fixed-wing ure constructed and arranged to carry a payload, an aircraft propulsion system d with the fixed-wing structure, and an engagement section coupled with the fixed-wing structure, the engagement section being constructed and arranged to engage with the aerial vehicle while the fixed-wing aircraft is propelled by the aircraft propulsion system during flight; the aerial vehicle including: a frame, an aircraft interface d with the frame, the aircraft interface being constructed and ed to physically interface with the fixed-wing aircraft, a set of rotor assemblies coupled with the frame, a set of wing surfaces that provides lift when the set of rotors provides thrust in a horizontal direction, and a controller supported by the frame, the controller being constructed and arranged to operate the set of rotor assemblies to provide the VTOL capabilities while the aircraft interface physically interfaces with the fixed-wing aircraft; wherein a r linkage-style hold/release assembly having a set of engaging mechanisms of the ft interface is constructed and arranged to extend from the set of wing surfaces to engage with an underside of the fixed-wing aircraft while the aerial vehicle and the fixed-wing aircraft fly a predefined distance apart from each other during horizontal flight.
21. The aerial vehicle as in claim 1 wherein the aircraft includes a fixed-wing structure constructed and arranged to provide lift to the aircraft during horizontal flight; and wherein the set of wing surfaces of the aerial vehicle in tandem with the fixed-wing ure of the aircraft are ucted and arranged to provide lift while the ft resides above the aerial vehicle and the aerial vehicle resides below the aircraft during horizontal flight.
NZ786029A 2020-09-30 Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities NZ786029B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US16/599,454 US11542004B2 (en) 2019-10-11 2019-10-11 Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities
PCT/US2020/053515 WO2021071718A1 (en) 2019-10-11 2020-09-30 Maneuverability involving a fixed-wing aircraft and an aerial vehicle having vertical takeoff and landing capabilities

Publications (2)

Publication Number Publication Date
NZ786029A NZ786029A (en) 2024-04-26
NZ786029B2 true NZ786029B2 (en) 2024-07-30

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