GB2471663A - Coanda effect vehicle - Google Patents

Coanda effect vehicle Download PDF

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Publication number
GB2471663A
GB2471663A GB0911668A GB0911668A GB2471663A GB 2471663 A GB2471663 A GB 2471663A GB 0911668 A GB0911668 A GB 0911668A GB 0911668 A GB0911668 A GB 0911668A GB 2471663 A GB2471663 A GB 2471663A
Authority
GB
United Kingdom
Prior art keywords
deflector
path
fluid
coanda
axis
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB0911668A
Other versions
GB0911668D0 (en
Inventor
Lee Whitcher
Steve Potter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aesir Ltd
Original Assignee
Aesir Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aesir Ltd filed Critical Aesir Ltd
Priority to GB0911668A priority Critical patent/GB2471663A/en
Publication of GB0911668D0 publication Critical patent/GB0911668D0/en
Priority to PCT/GB2010/051115 priority patent/WO2011004187A2/en
Publication of GB2471663A publication Critical patent/GB2471663A/en
Withdrawn legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C29/00Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/001Flying saucers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/06Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/062Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
    • B64C39/064Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings with radial airflow
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15DFLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00Influencing flow of fluids
    • F15D1/10Influencing flow of fluids around bodies of solid material

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Body Structure For Vehicles (AREA)

Abstract

A Coanda vehicle comprises a canopy 1 having an upper convex surface 7 and an impeller 2, 5. Features 1, 3 are provided which define a path for fluid which passes through the impeller and curves from a relatively axial direction to a relatively radial direction, the path terminating at a position adjacent the surface 7 so that fluid flow over the surface 7 produces lift. A deflector 8 is located in the path so that fluid flows over opposite surfaces of the deflector 8, the deflector 8 being curved in the same direction as the curvature of the path. By employing the invention it becomes possible to change the velocity profile across the fluid path, thus offering a potential for improved performance. The vehicle is typically an air vehicle, but may alternatively be for use under water.

Description

Coanda Effect Vehicle This invention relates to an air vehicle of the type that uses the Coanda Effect to divert a flow of fluid thereby producing lift.
The Coanda effect is a phenomenon which tends to keep a jet of fluid attached to a surface over which it flows. In the case of a Coanda effect air vehicle, the jet of fluid is an air flow and this can be produced using an axial fan or by a radial fan.
Coanda effect air vehicles are capable of hovering and have advantages over conventional hovering vehicles. For example, they can operate safely close to vertical surfaces. Also, the "canopy" that is responsible for the Coanda effect provides a natural enclosure for the payload. However, as with all air vehicles, a fundamental design problem always present is to achieve greater net lift. The present invention addresses this problem in Coanda craft.
In general it has been found that axial fans are better for larger Coanda craft whilst radial fans are better for small craft. In both cases, the air enters the fan in a generally axial direction i.e. parallel to the axis of rotation of the fan blades but is diverted radially before flowing over the surface responsible for producing lift. n the case of an axial fan, this diversion of the flow towards the radial direction occurs downstream of the fan blades whereas, for a radial fan, the diversion occurs upstream of the fan.
In a typical axial fan arrangement, the axially flowing air stream from the fan is diverted to the radial direction by an annular duct defined between a canopy of the craft and a shroud spaced above it. Measurements of air flow, in such a craft at the outlet of the duct, have shown that the velocity is greatest close to the canopy and is least close to the shroud; and that turbulence can occur at the latter position.
According to the invention there is provided a Coanda vehicle comprising a canopy having an upper convex surface, an impeller, means defining a path for fluid which passes through the impeller and curves from a relatively axial direction to a relatively radial direction, the path terminating at a position adjacent the said surface so that fluid flow over the surface produces lift characterised by a deflector located in the said path so that fluid flows over opposite surfaces of the deflector, the deflector being curved in the same direction as the curvature of the path.
By employing the invention it becomes possible to change the velocity profile across the fluid path, this offering a potential for improved performance. Preferably the deflector is arranged so as to create a more uniform velocity of flow with respect to height above the Coanda surface and has been found that this is especially beneficial in achieving improved lift. However there may be benefits in making the arrangement so that the velocity decreases towards the surface.
In most cases the curved surface responsible for producing the lift will extend around a central axis. The airstream will be directed into an annular shape so as to flow over this surface and the deflector will preferably have a corresponding annular shape so as to be effective around the whole of the annular airstream. There are other possibilities. For example, the deflector could be formed from a series of individual segments arranged around the axis.
The fact that the deflector has a significant effect on lift can be used to control the vehicle. Tn such an arrangement, the deflector would be adjustable. For example, where the deflector is in the form of an annular ring, it could be mounted on three or more adjustable posts so that its axis could be swivelled relative to the axis of the fan.
An example of one way in which the invention may be performed will now be described with reference to the accompanying drawings in which: -Fig 1 is a perspective view, shown partly broken away to reveal interior details of an air vehicle constructed in accordance with the invention; Figs 2A and 2B are schematic diagrams illustrating the effect of a deflector included in the vehicle shown in Fig 1; and Fig 3 is a block diagram showing a control system for the vehicle of Fig 1.
Referring to Fig 1 there is shown a vertical take off aircraft having a canopy 1 defining an aerodynamic surface of double convex curvature and an axial fan 2. The fan is driven by an engine or motor, not illustrated, housed within the canopy 1. The fan 2 and the canopy 1 have a common axis of symmetry X -X. A shroud 3 is supported by struts 3A above the canopy and extends circumferentially around the fan 2 such as to define a duct 4 within which the fan 2 is housed.
Air is drawn axially into the fan 2 along the axis as indicated by the arrows 5 and is expelled as a radial jet 6 over a surface 7 of the canopy, this surface having double convex curvature. By virtue of the Coanda effect the jet follows the curve of canopy, diverted from an approximately radial direction, towards an approximately axial direction; and the jet finally parts from the canopy surface at its lower edge 8. This diversion of the jet towards the vertical axis generates vertical lift.
Because of the rotary action of the fan 2, the air expelled from it has a circumferential velocity component. The struts 3A are designed as aerofoils, angled to counteract this effect and have adjustable vanes 3B to control yaw, i.e. rotation about the axis X -X. Downstream of the fan 2, the duct 4 is curved to divert the air stream from an axial direction to a radial direction. In this curved region is located an annular deflector 8 mounted on three supporting posts 9 (only one visible on Fig 1) spaced equidistantly about the axis X -X. The supporting posts normally hold the deflector in a datum position where its axis is the same as axis X-X. However, each post 9 can be adjusted, using actuators 10, so as to tilt the axis of the deflector relative to the main axis X -X. A cross-section of the deflector 8, through a plane of the axis X -X, is curved so as to follow the curvature of the duct 4. In the illustrated embodiment, the curvature of the deflector is approximately such as to follow the mid point between the canopy and the shroud but this is not essential and some beneficial effect can be expected providing there is some curvature in the same direction.
Measurements of air velocity have been made at the output of the duct 4 i.e. at the upstream end of the jet of air passing over the Coanda surface 7. Fig 2A shows these measurements when the deflector 8 was removed whilst Fig 2B shows measurements made with the deflector 8 in position. From Fig 2 it can be seen that an uppermost region R of the jet stream, adjoining the downstream edge of the shroud is subject to turbulence, resulting in a backward or negative flow velocity. This significantly degrades the lift of the craft as compared with the arrangement where the deflector 8 is in position as shown in Fig 2B where there is no area of negative velocity flow.
Fig 3 shows a microcontroller 11 and an inertial measurement unit (IMU) 12, housed within the canopy 1. The IMU is conventional and includesgyros, accelerometers and magnetometers to obtain an accurate estimate of the aircraft's instantaneous attitude/orientation defined as angles of pitch, roll and yaw. The microcontroller receives instruction signals from a user interface 13 via a communication channel 14.
These instruction signals represent the desired pitch, roll and yaw angles of the craft.
To understand these angles it is helpful to designate a particular point on the canopy 7 as being the "front" of the craft. Yaw is any angle of rotation about the X -X axis of the front of the craft relative. Pitch is the angle by which the axis X -X is displaced from the vertical in a plane passing through the axis and the front of the craft. Roll is the angle by which the axis X -X is displaced from the vertical in a plane passing through the axis and normal to the aforementioned plane.
Using the output from the IMU 12 as a reference, the microcontroller 11 compares the desired yaw angle with the actual yaw angle (this is the angle of rotation about the axis X -X) and produces an error signal that operates actuators 3C, located within the shroud 3, to adjust the vanes 3B (Fig 1) until the error signal reaches zero.
Normally these error signals will be identical so that the vanes 3B are adjusted in synchronism. However it is possible to introduce a differential between these signals causing the vanes 3B to be deflected differently thereby supplementing the pitch and roll adjustment to be described in the following paragraph.
The microcontroller 11 also compares the desired pitch and banking angles with those detected by the IMU 12 and generates correction signals to operate the actuators 10.
These actuators are thereby caused to change the axis of the deflector 8 to produce the required change in roll and pitch angles.
If the aircraft is to employ an Automatic Flight Control System (AFCS), the instruction signals fed from line 14 to the microcontroller will be automatically calculated by some mathematical algorithm as opposed to being manually inputted by a pilot. This algorithm will take into account such factors as aircraft attitude, heading, its inherent dynamics, and desired location in its calculation of instruction signal. The manner in which the aircraft responds to an error signal is dependent upon the aircraft's inherent dynamics and, as such, the AFCS can be tuned to manipulate the instruction signal to achieve an optimal response. Higher level control will enable the aircraft to automatically fly between waypoints and respond to unpredictable events such as the introduction of an obstacle or terrain anomaly. In addition, an external human operator will be able to override the predetermined flight plan with manual commands which, rather than take direct control over the aircraft itself, inform the AFCS of a new desired position. This operation will be performed dynamically and remotely in a manner known in the field of aircraft control systems via some wireless telemetry system.
The inclusion of the deflector 8 in a craft like that illustrated has been shown to improve its performance very significantly. However, the illustrated craft represents just one way in which the invention may be used. There are many variations within the scope of the invention as defined by the accompanying Claims. For example, it would be possible to include more than one vane, one above the other; and, where a radial, rather than an axial fan is employed, the deflector could be positioned upstream of the fan so as to continue to produce its beneficial effect where the air flow is diverted from the axial to radial direction. Other possible variations include the use of a combustion jet instead of a fan, and the use of the invention in underwater craft instead of air vehicles.

Claims (4)

  1. Claims 1. A Coanda vehicle comprising a canopy having an upper convex surface, an impeller, means defining a path for fluid which passes through the impeller and curves from a relatively axial direction to a relatively radial direction, the path terminating at a position adjacent the said surface so that fluid flow over the surface produces lift characterised by a deflector located in the said path so that fluid flows over opposite surfaces of the deflector, the deflector being curved in the same direction as the curvature of the path.
  2. 2. A Coanda air vehicle according to Claim 1 characterised in that the impeller is an axial fan and that the deflector is arranged downstream of the fan.
  3. 3. A Coanda vehicle according to Claim 1 or 2 characterised in that the fluid path and the deflector arc annular.
  4. 4. A Coanda vehicle according to Claim 3 characterised by an adjustment mechanism whereby an axis of the deflector can be varied relative to an axis of a stream of fluid.
GB0911668A 2009-07-06 2009-07-06 Coanda effect vehicle Withdrawn GB2471663A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB0911668A GB2471663A (en) 2009-07-06 2009-07-06 Coanda effect vehicle
PCT/GB2010/051115 WO2011004187A2 (en) 2009-07-06 2010-07-06 Coanda effect vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0911668A GB2471663A (en) 2009-07-06 2009-07-06 Coanda effect vehicle

Publications (2)

Publication Number Publication Date
GB0911668D0 GB0911668D0 (en) 2009-08-12
GB2471663A true GB2471663A (en) 2011-01-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
GB0911668A Withdrawn GB2471663A (en) 2009-07-06 2009-07-06 Coanda effect vehicle

Country Status (2)

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GB (1) GB2471663A (en)
WO (1) WO2011004187A2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3398852A1 (en) * 2017-05-01 2018-11-07 Ecotech Engines AG Method and device for creating a lifting force on a wing-disc transport apparatus
DE102019000682A1 (en) * 2019-01-30 2020-07-30 Claudia Meier Missiles for transport and traffic

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
WO2017065858A2 (en) 2015-09-02 2017-04-20 Jetoptera, Inc. Ejector and airfoil configurations
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
JP7155174B2 (en) 2017-06-27 2022-10-18 ジェトプテラ、インコーポレイテッド Aircraft vertical take-off and landing system configuration
CN111204455B (en) * 2020-03-12 2023-01-03 王略 Disc-wing aircraft

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB431646A (en) * 1934-01-08 1935-07-08 Henri Coanda Improvements in or relating to the propulsion of solid bodies in fluid media
US3747726A (en) * 1971-12-10 1973-07-24 W Walter Ground effect vehicle
US4941628A (en) * 1988-02-02 1990-07-17 Kabushiki Kaisha Kobe Seiko Sho Lift generating apparatus, in aircraft employing the lift generating apparatus, and a lift generating method
US5803199A (en) * 1994-05-02 1998-09-08 Hybricraft, Inc. Lift augmented ground effect platform
JP2009029400A (en) * 2007-06-22 2009-02-12 Toyota Motor Corp Flying unit

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US2996266A (en) * 1958-03-20 1961-08-15 Rebasti Antonio Device for obtaining the sustentation of supporting surfaces of aircraft
US3107071A (en) * 1961-01-05 1963-10-15 Wessel J O Wessels Vertical take-off and landing aircraft
US7147183B1 (en) * 2004-01-22 2006-12-12 Robert Jonathan Carr Lift system for an aerial crane and propulsion system for a vehicle
CZ300629B6 (en) * 2007-08-22 2009-07-01 Janda@Zdenek Aircraft using for flight wall jet in order to generate lifting force
SK288178B6 (en) * 2008-01-02 2014-04-02 Marian Pružina Spring flying device

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB431646A (en) * 1934-01-08 1935-07-08 Henri Coanda Improvements in or relating to the propulsion of solid bodies in fluid media
US3747726A (en) * 1971-12-10 1973-07-24 W Walter Ground effect vehicle
US4941628A (en) * 1988-02-02 1990-07-17 Kabushiki Kaisha Kobe Seiko Sho Lift generating apparatus, in aircraft employing the lift generating apparatus, and a lift generating method
US5803199A (en) * 1994-05-02 1998-09-08 Hybricraft, Inc. Lift augmented ground effect platform
JP2009029400A (en) * 2007-06-22 2009-02-12 Toyota Motor Corp Flying unit

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3398852A1 (en) * 2017-05-01 2018-11-07 Ecotech Engines AG Method and device for creating a lifting force on a wing-disc transport apparatus
DE102019000682A1 (en) * 2019-01-30 2020-07-30 Claudia Meier Missiles for transport and traffic
DE102019000682B4 (en) 2019-01-30 2022-07-14 Kmtc Vortifer Projektgesellschaft Mbh Missiles for transport and traffic
US11851182B2 (en) 2019-01-30 2023-12-26 Kmtc Vortifer Projektgesellschaft Mbh Aircraft and method for operating an aircraft

Also Published As

Publication number Publication date
WO2011004187A2 (en) 2011-01-13
WO2011004187A3 (en) 2011-03-31
GB0911668D0 (en) 2009-08-12

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