GB2387158A

GB2387158A - Aerial flying device

Info

Publication number: GB2387158A
Application number: GB0204854A
Authority: GB
Inventors: Robert John Collins
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-03-01
Filing date: 2002-03-01
Publication date: 2003-10-08
Anticipated expiration: 2022-03-01
Also published as: GB2387158B; GB0204854D0

Abstract

A powered aerial device able to ascend, descend, and move in any horizontal direction. The device may have a body 1 of circular, oval or polygonal plan form with a special convex curved upper surface 1a. Air above the aerial device is drawn axially into a radial disk fan 2 which is powered by a motor 5, and accelerated radially over the upper surface 1a of the body 1 and which attaches by boundary layer effects to the upper surface 1a resulting in lift being imparted to the aerial device. A motor torque cancellation and steering device 8 is included as well as a localised air stream detachment means 6, which controls lift and horizontal propulsion. The localised air stream detachment means 6 is controlled by independent actuators 7. Lift and steering is controlled by disturbing the boundary layer air stream over the upper surface 1a.

Description

23871 58

IMPROVEMENTS TO AERIAL DEVICES

The present invention relates to improvements to aerial devices of the type that employ an aerodynamic boundary layer flowing radially over a downwardly curved surface to effect lift. There are many examples of aerial device but most fall into one OI several categories.

Kites for example take many forms but may be categorised as tethered. Tethering ensures that the kite is controlled and thereby flight is sustained Kites rely on a tether to sustain a controlled attitude to a prevailing wind and the energy to sustain the flight is drawn from the wind.

Aerial balloons are another category which may or may not be tethered but rely on the natural buoyancy of certain gases. Controllable and steerable balloons are of course well known. Gliders form a category of many types and are well known. Gliders are generally distinguished from kites by virtue of their non-reliance on tethering to sustain controlled flight but rather rely on aerodynamic characteristics and possibly employ moveable or adjustable control surfaces. Energy to sustain flight is drawn from either exploiting the natural movement of the air or by the use of a tether to a power source, which may be a winch or perhaps a powered aircraft for example, Another category of aerial device use the parachute principle which ensures a minimal rate of descent by means of a canopy presenting the maximum cross sectional area and hence air resistance to the descent path. The payload, situated some distance beneath the canopy ensures a low centre of gravity to provide stability,

Generally, parachutes only descend and do not normally ascend unless some control mechanism such as a tether or tow is employed or they are launched in an upward direction and may act as a glider and rely on natural air movement to ascend.

The "Frisbee", some times referred to as a disk wing, falls into the later category but with slight modification. Axial spin is imparted at its launch and so it is not dependent on a payload for stability. Its rate of descent is retarded as its spin ensures that it presents the maximum air resistance to the descent path.

Model or toy aeroplanes, darts and helicopters employing conventional "tear drop" aerofoils form another category and are of course well known although very simple toys may rely just on angled propulsion and control surfaces such as may be used in a wound rubber powered model or a folded paper dart for example Flapping wing aerial devices or ornithopters is yet another category of aerial device which attempt to emulate the wing action of birds, flying reptiles or flying insects.

Ornithopters are a well-known novelty Rocket or thrusters propelled aerial devices might be regarded as yet another category particularly if they are equipped with aerodynamic control surfaces or other control means. A note worthy feature of many aerial devices is the employment of the "tear drop" or conventional aerofoil, that is bulbous at the leading edge and trailing to a thin section.

There are many aerofoil sections suited to special applications but they all fit the general description of a teardrop.

Depending on the application, the conventional aerofoil may be symmetrical or asymmetrical about an imaginary line termed the Cord line drawn from front to rear of the section.

Such aerofoils are widely used in many types of aerial device and whilst this is known to be an important developments it has one significant shortcoming. The aerofoil section best suited to provide lift for aerial devices is asymmetrical because it creates unbalanced forces when moved through the air or when air is forced over it and providing the aerofoil is suitable orientated, the force acting on the upper surface of the aerofoil caused by the air moving over it and resulting in an upwardly directed force on the aerofoil is greater than the downwardly acting force on the lower surface of the aerofoil when similarly exposed to relative air flow. This is achieved by such means as making the aerofoil asymmetric about its chord line and adjusting the angle that the chord line makes with the air stream.

The conventional aerofoil is a highly developed means of generating aerodynamic forces but the aerofoil would be much more effective in providing lilac if there where no lower surface but this is not possible in a conventional aerofoil.

Vertical ascending and descending aerial devices are well known ranging from toys and novelties to large aircraft of which the most well known is the helicopter but there are other types such as reconfigurable aircraft that resemble aeroplanes but with aerofoil propellers or jet engines or thrusters that may be rotated about their lateral axes to provide lift and hence vertical take off and landing and when airborne, reconfigure to effect forward horizontal flight.

There are other types that rely on directable jets or rocket thrusters to provide lift for vertical take off and landing and which may subsequently rely on fixed aerofoils to provide lift for forward horizontal flight.

Helicopters rely on conventional adjustable pitch aerofoils to provide lift to effect vertical take off and landing. The aerofoils of course rotate but in order to effect control of the lift force the pitch of the aerofoil is adjustable. Vertical take off and landing as well as hovering are effected by the collective control of the pitch of the aerofoils making up the rotor assembly.

The need for collective pitch control of the aerofoils necessitates a complex arrangement of linkages and thrust plates, which connect the rapidly moving aerofoils to static controls, as may be handled by a pilot or by other means. This difficulty is further exacerbated by the need to effect cyclic control of the aerofoil pitch to effect horizontal motion. In the case of reconfig,urable aeroplanes, whilst lift during take off and landing is provided by the rotating aerofoils or jet engine thrusters directed in a vertical or substantially vertical attitude, once airborne lift is sustained by conventional fixed aerofoil wings and the rotating aerofoils or jet engine thrusters are used for propulsion.

This results in extremely complex mechanisms necessitating very sophisticated control systems in order to transition from vertical take off to horizontal flight and when transitioning from horizontal flight to the hover for vertical landing.

The mechanisms and control systems of such aircraft are further complicated if during hover, sideways or lateral movement is desired which usually involves cyclically

An adjusting the pitch of the rotating aerofoils providing lift as is necessary with the helicopter or to redirect jet engine thrusters that may be providing the lift force.

The invention to which these improvements apply, as well as the present invention, do not rely on conventional aerofoils for lift either by way of rotating or fixed wing or jet engine thrusters and consequently do not suffer from the disadvantage of complex control systems to effect collective and cyclic aerofoil pitch changes of the type employed by helicopters or reconfigurable aeroplanes to control the degree of lift or to redirect jet engine thrusters that may be providing the lift force.

The basic principle of vertical take off and landing aerial devices relying on vectoring jets or rocket thrusters is obvious. The downward force resulting from the directed jets or thrusters results in an upward reaction or lift, to the device.

It must be acknowledged however, that when this principle is applied to an aircraft that whilst the basic concept of such aircraft is obvious, the control of such mechanisms in order to achieve stable vertical take off and landing and transition to horizontal flight from the hover mode is extremely complex.

The invention to which these improvement apply, as well as the present invention, do not rely on vectoring jets or thrusters to generate lift and consequently the control system is thus greatly simplified.

Steering a helicopter is usually effected by means of powered active rudders or vectoring jets or thrusters, which may also serve to counter torque forces resulting from the aircraft's power unit.

Active rudders which depend on rotating aerofoils are complicated mechanical devices requiring parts that are in rapid motion to be adjusted which means that in some way

Am these parts have to be mechanically linked by slipping joints or thrust plates to parts which are not in rapid motion and which may be employed by a pilot or other means to effect directional control of the aircraft which requires considerable skill on the part of the .. pact or conrrolier.

Helicopters with twin axial aerofoil rotors may not require torque cancellation due to the use of counter rotating aerofoil rotors but commonly they still require some sort of active rudder be it rotating aerofoils or vectoring jets or thrusters.

Helicopters with two or more aerofoil rotors, but which are not coaxial, may not require torque cancellation due to their use of counter rotating aerofoil rotors but steering is effected by varying the pitch of the aerofoils cyclically in one or perhaps both of the aerofoil rotors and consequently suffer from the need to incorporate complex linkages Two methods of steering reconfigurable aeroplanes is necessary depending on the flight mode Because such aircraft do not generally employ active rudders or vectoring jets or thrusters in the vertical ascent or descent modes for steering, steering is effected by cyclic pitch adjustment of the rotating aerofoils providing lift in this mode or to redirect jet engine thrusters that may be providing the lift force ADer transition into the ordinary horizontal flight mode, such aircraft rely on the normal means of steering conventional aircraft, that is the use of passive aerofoil rudders Such dual modes of flight result in the necessity for dual types of flight control, one for the vertical ascent and descent mode employing cyclic control of the rotating aerofoil pitch or to redirect jet engine thrusters that may be providing the lift force and another for the normal aeropiane mode

Am) This results in dual complex control mechanisms and high degrees of human skill to effect satisfactory flight.

The present invention uses a single, simple mechanism to effect control for all flight modes Steering of vertical ascent aircraft relying on vectoring jets or rocket thrusters for lift is effected by directing thrust by way of a propellant or by way of directed air mass in the direction opposed to the desired direction of travel.

The present invention does not require active rudders for steering or torque cancellation.

Neither does it does it rely on vectoring jets or rocket thrusters In addition, whilst in a particular embodiment it may be preferred to employ rotating aerofoils or vectoring jets or thrusters for propulsion, there is no necessity for rapidly rotating aerofoils, vectoring jets or thrusters to effect steering or torque cancellation, which results in a greatly simplified steering mechanism.

In the present invention, steering and motor torque cancellation may be controlled by a single passive means making the coupling between rapidly moving parts and parts not in rapid motion unnecessary and thus greatly simplifying the steering and torque cancellation mechanism.

In the present invention, lift as well as horizontal propulsion may be controlled by a single passive means making the coupling between rapidly moving parts and parts not in rapid motion unnecessary and thus greatly simplifying the lift and propulsion mechanism.

The present invention, whilst it is not reliant on vectoring jets or thrusters to effect steering or torque cancellation, may employ such means in a particular embodiment for steering or propulsion.

Horizontal flight of helicopters is effected by either cyclically varying the pitch of the rotating aerofoils providing lift or by horizontally disposed rotating aerofoils or jet thrusters. In the case of horizontal motion being effected by cyclically varying the pitch of the rotating aerofoils providing lift, that is to say that during an aerofoil's rotational cycle its pitch, the angle that the Chord line makes to the horizontal, is varied such that a greater lift force is created on the aerofoil at one part of its rotation than at another part of its rotational cycle.

This results in a tendency for the aerofoil to tilt upwards about its rotational centre when it is so subjected to a greater lift force at one position during its rotational cycle and a tendency to tilt downwards when it is another part of its rotational cycle.

This tilting of the aerofoil rotor results in a horizontal reaction being imparted to the aircraft thus resulting in forward motion.

The means by which cyclic control of the aerofoils and hence horizontal motion of the aircraft is effected in this case necessitates complicated linkage mechanisms which facilitate the coupling of parts of the aerofoil rotor which are in rapid motion to controls which are not in rapid motion and may be used to effect horizontal movement of the aircraft by a pilot or by other means.

A further consequence of tilting the aerofoil rotor to effect horizontal movement of helicopters is that a complicated hinge mechanism has to be incorporated at the aerofoil's root to prevent the main body of the aircraft from tilting with the aerofoil rotor and thus presenting less than the optimum aerodynamic profile for forward motion.

Whilst the present invention may effect horizontal movement by employing a tilting action to parts of the device, those parts are not in rapid relative motion to the control means and hence complicated coupling mechanisms are unnecessary and the means of effecting horizontal motion is greatly silllpliried. In additio,., because there are no aerofoils requiring cyclic change of pitch there is no necessity to incorporate flapping hinges to maintain the body of the aerial device in a horizontal attitude for forward flight.

In order to effect horizontal flight of reconfigurable aeroplane type aircraft employing rotating aerofoils or redirectable jet engine thrusters that may be providing the lift force, it is necessary to transition from the vertical ascent and descent flight mode This involves laterally rotating the aerofoil rotor or redirectable j et engine thrusters in such a way that they continue to provide sufficient lift until the aircraft attains sufficient forward velocity to enable the fixed aerofoil wings of the aircraft to sustain the aircraft in forward flight.

There is no necessity for the present invention to reconfigure in order to transition from the vertical ascent and descent mode to the horizontal flight mode The aerial device to which these improvements apply differs significantly from all of the categories so far described and differs in many respects from other aerial devices in so far as it does not depend on conventional aerofoils to generate lift nor suffer from the disadvantage that such aerofoils present from their dependence on a lower surface.

Neither does it depend on jet thrusters or flapping wings or the natural movement of the surrounding air or the buoyancy of gasses to effect lift.

According to the present invention there are provided improvements to vertical ascending and descending aerial devices of the type with circular, oval or polygonal plan form with a special convex curve to their upper surface that are able to ascend in a controlled manner by means of the surrounding air at the top being drawn into and accelerated over

An) the curved upper surface and which attaches to the downwardly curved upper surface by aerodynamic effects and provides an upwardly directed reaction as it leaves the lower rim of the aerial device These improvements are by the addition of certain features that provide motive power, facilitate control of direction of horizontal movement, control of lift for ascent and descent and directional attitude such that the aerial device is capable of controlled ascent, descent and horizontal flight in any direction comprising a motor, to power the air accelerating means which is typically a disk fan but may be any suitable means of accelerating air in this manner, a motor torque cancellation and steering device, a localised air stream detachment means and control actuators to control the air stream detachment means.

The rate of ascent or descent of the aerial device may be controlled by varying the rotational speed of the motor or air accelerating means or restricting the airflow into the air accelerating means.

In one embodiment of the invention, the rate of ascent and descent is controlled by locally detaching the accelerated air stream caused to flow over the upper surface of the body by the action of the air accelerating means In one embodiment of the invention, the motor torque cancellation and steering device comprises a number of yaw adjustable aerofoils disposed vertically about the air accelerating means. Air leaving the accelerating means passes between the aerofoils and by suitably adjusting their angle of yaw to the accelerated air stream then a motor torque countering force may be generated on the aerofoils which are mounted pivotally to the body of the aerial device which ensures that the torque countering force is transmitted to the body of the aerial device

Similarly, to effect steering of the aerial device, the angle of yaw of the aerofoils may be increased or decreased thus causing the aerial device to tend to rotate in a chosen direction about its vertical axis by the same mechanism.

In one embodiment of the invention, horizontal movement of the aerial device is effected by locally detaching the accelerated air stream caused to flow over the upper surface of the body by the action of the air accelerating means. This causes the lift on one side of the aerial device to be greater than on its opposite side and thus the aerial device tilts. The consequence of the tilt is that the accelerated air stream over the body is now directed in a more horizontal direction than on the other side of the aerial device and thus there is a net component of horizontal force acting on the aerial device, which causes it to accelerate in the same direction as the acting force.

In this embodiment of the invention, the means by which the localised detachment of the air stream caused to flow over the upper surface of the body by the action of the air accelerating means is effected by a horizontal aerofoil disposed as a ring around the air accelerating means and is controlled by independently acting actuators or by other means.

A specific embodiment of the invention, will be described below by way of example only with reference to figures 1 to 21 of the accompanying drawings, wherein: Figure 1 is a is an isometric view from above of an aerial device to which these improvements apply showing the body 1, the convex upper surface la, the lower rim lb of the body, air accelerating means which in this example is a disk fan 2 and its direction of rotation is as indicated by the curved arrows.

By) Figure 2 is a sectional view of an aerial device to which these improvements apply showing the body 1, the upper surface 1 a of the body and the lower rim I b of the body and disk fan air accelerating means 2.

Figure 3 is isometric partial view from above of the an aerial device to which these improvements apply showing the disk fan air accelerating means and the direction of rotation is as indicated by the curved arrows.

Figure 4 is an isometric view from above of an aerial device to which these improvements apply illustrating by means of downwardly pointed arrows how ambient air is drawn coaxially into the disk fan air accelerating means 2.

Figure 5 is an isometric view from above of an aerial device to which these improvements apply illustrating by means of outwardly radial pointed arrows how air is accelerated by the disk fan air accelerating means 2 and downwardly deflected over the upper surface la of the body 1 by aerodynamic or boundary layer effects and how it detaches at the lower rim 1 b of the body 1.

Figure 6 is an isometric view from above of the aerial device to which these improvements apply illustrating by means of downwardly pointed arrows how ambient air is induced to enter the air stream accelerated by and leaving the periphery of the disk fan air accelerating means 2 over the upper surface 1 a of the body 1.

Figure 7 is an isometric view from above of an aerial device to which these improvements apply, illustrating by means of arrows how ambient air is drawn coaxially into the disk fan air accelerating means 2 and accelerated radially and downwardly deflected over the upper surface 1 a of the body 1 and how ambient air is induced to enter the accelerated air

If stream over the upper surface la of the body 1 and detach from the upper surface la at the lower rim lb of the body 1.

Figure 8 is a side elevation of an aerial device to which these improvements apply illustrating by means of arrows how ambient air is drawn coaxially into the disk fan air accelerating means 2 and accelerated radially and downwardly deflected over the upper surface 1 a of the body 1 and how ambient air is induced to enter the accelerated air stream over the upper surface 1 a of the body 1 and detach from the upper surface at the lower rim lb of the body 1 as in figure 7.

Figure 9 is a side elevation of the aerial device to which these improvements apply as in figure but with all arrows illustrating airflow removed for clarity.

Figure 10 is a sectional view of a further embodiment of the aerial device to which these improvements apply with the disk fan air accelerating means 2 attached by an axle 3 and bearing 4 to the body 1 such that the disk fan air accelerating means 2 may rotate with respect to the body 1.

Figure 11 is a sectional side view of the present invention illustrating the addition of a motor 5, the torque cancellation and steering device 8, the localised air stream detachment aerofoil means 6, and detachment aerofoil control actuators 7 by way of improvements.

Figure 12 is an isometric sectional view of the present invention illustrating the relationship between the torque cancellation and steering device 8, the localised air stream detachment aerofoil means 6, the detachment aerofoil control actuators 7 and a disk fan air accelerating means 2 Figure 13 is an isometric partial view of the present invention illustrating the relationship between the torque cancellation and steering device 8 and a disk fan air accelerating

means 2. The torque cancellation and steering device 8 comprises a number of yaw adjustable aerofoils 8a, disposed vertically about the disk fan air accelerating means 2, and the yaw adjustable aerofoils control ring 8b. The direction of rotation of the air accelerating means disk fan 2 is indicated by CUI red al'o-ws.

Figure 14 is isometric view of the present invention from above illustrating the body l, the torque cancellation and steering device 8, the localised air stream detachment aerofoil means 6 and their relationship to the disk fan air accelerating means 2 Figure 15 is an isometric sectional view of the present invention illustrating the motor 5, the torque cancellation and steering device 8, the localised air stream detachment aerofoil means G. the detachment aerofoil control actuators 7, the special curvature of the upper surface la and the upper surface lower rim lb and their relationship to the disl; fan air accelerating means 2.

Figure 16 is a plan view of the present invention illustrating the body 1, the torque cancellation and steering device 8, the localised air stream detachment aerofoil means 6 and their relationship to the disk fan air accelerating means 2.

Figure 17 is a plan view ofthe ofthe present invention illustrating the action ofthe torque cancellation and steering device 8 by means of radially pointing arrows representing part of the accelerated air stream from the disk fan air accelerating means 2 flowing over a section of the upper surface 1 a of the body 1, causing the aerial device to rotate in a counter clockwise direction, as indicated by the curved arrows, about its vertical axis by virtue of the force exerted on the yaw adjustable aerofoils 8a Figure 18 is a plan view of the of the present invention illustrating the action of the torque cancellation and steering device 8 by means of radially pointing arrows representing part

of the accelerated air stream from the disk fan air accelerating means 2 flowing over a section of the upper surface la of the body 1, causing the aerial device to rotate in a clockwise direction, as indicated by the curved arrows, about its vertical axis by virtue of the lance easel Led Oll 'he yaw adj-ustab'e aerofoil Sa Figure 19 is a sectional view of the present invention illustrating the action of the localised air stream detachment aerofoil means 6, and the detachment aerofoil control actuators 7. In this illustration the localised air stream detachment aerofoil means 6 is inclined by means of the detachment aerofoil control actuators 7 such that the accelerated air stream, illustrated by means of arrows, is deflected over the localised air stream detachment aerofoil means 6 on one side ofthe aerial device and thus is detached from the upper surface la of the body 1. Whereas, on the opposite side, the accelerated air stream passes under the localised air stream detachment aerofoil means 6 and thus attaches to the upper surface la of the body 1 and consequently follows the special downward curvature of the upper surface la of the body l.

Figure 20 is a sectional view of the present invention illustrating the action of the localised air stream detachment aerofoil means 6, and the detachment aerofoil control actuators 7. In this illustration the localised air stream detachment aerofoil means 6 is uniformly lowered by means of the detachment aerofoil control actuators 7 such that accelerated air stream, illustrated by means of arrows, is deflected over the localised air stream detachment aerofoil means 6 on both sides of the aerial device and thus is detached from the upper surface la of the body 1 over the whole of the upper surface la of the body l.

Figure 21 is a sectional view of the present invention illustrating the action ofthe localised air stream detachment aerofoil means 6, and the detachment aerofoil control

: 16 actuators 7. In this illustration the localised air stream detachment aerofoil means 6 is uniformly raised by means of the detachment aerofoil control actuators 7 such that accelerated air stream, illustrated by means of arrows, is allowed to flow under the !oGalised air stream detashm.ent aerofoi1 means 5 on both sides of the aerial device and thus follows the special downward curvature of the upper surface l a of the body 1.

Referring to figure 1 isometric view and figure 2 sectional view, the aerial device to which these improvements apply has a disk or polygonal plan form body 1 and is essentially a thin shell type structure with convex upper surface la and a lower rim lb with a radial air accelerating means situated at the top.

IN one embodiment of the aerial device to which these improvements apply, situated at the centre of the upper surface la of the body 1 and mounted rigidly thereto, the radial air accelerating means is a disk fan 2.

In another embodiment of the aerial device to which these improvements apply, the radial air accelerator means is a disk fan 2 mounted rotatably to the body 1.

Referring to figures 1 and 2 sectional view and figure 4 isometric view of the aerial device to which these improvements apply, the upper surface la of the body 1 is curved in a particular convex profile and is of such a surface texture as to enhance the boundary layer attachment of air caused to flow over the upper surface 1 a radially by virtue of the disk fan air accelerating means 2. The upper surface 1 a of the body 1 curves downward toward a lower rim lb and is of such a design that air flowing over theupper surface la radially from its centre at the top by virtue of the disk fan air accelerating means 2 attaches to the upper surface la by boundary layer effects and readily detaches from the upper surface 1 a at its lower rim l b moving in a downward or substantially downward direction. Thus when sufficient angular momentum is imparted to the disk fan air

\ accelerating means 2 in the direction, indicated by curved arrows in figure 1, ambient air is drawn into the top of the disk fan air accelerating means 2 and is caused to be accelerated radially outwards thereby across the upper surface 1 a of the body 1.

Referring to figure 3 and 4, in the embodiment of the aerial device to which these improvements apply, the disk fan air accelerating means 2 rotates at high speed in the direction indicated and is so designed that ambient air is caused to be drawn into it coaxially until it is forced to leave at the periphery of the disk fan air accelerating means 2 by virtue of the radial acceleration imparted to it thereby. The air drawn coaxially into the disk fan air accelerating means 2 is illustrated by downwardly pointed arrows.

Referring to figures 1 and sectional view 2, in one embodiment of the aerial device to which these improvements apply, it is caused to ascend by imparting rotational spin to the disk fan air accelerating means 2 about the vertical axis in the direction indicated and the angular momentum so imparted is sufficient to sustain the ascent until the kinetic energy is dissipated at which time the aerial device commences to descend.

Referring to figure 4, in the embodiments of the aerial device to which these improvements apply so far described, the reaction to ambient air being drawn into the disk fan air accelerating means 2 at its top, as illustrated by the downward pointed arrows, results in a component of lift force being imparted to the aerial device by virtue of the coupling between the disk fan air accelerating means 2 and the body 1.

Referring to figure 5, the accelerated air being forced to flow radially over the upper surface la of the body 1 and downwardly deflected over the upper surface la of the body 1, by the action of the disk fan air accelerating means 2, as illustrated by means of outwardly radially pointed arrows, forms a laminar boundary layer which attaches to the

upper surface l a of the body 1, by virtue of boundary layer elects, as it flows outwards across the upper surface 1 a and detaches from the body 1 at its lower rim 1 b.

The boundary layer tends to exhibit laminar flow at its interface with the upper surface la of the body 1 but is inclined to become turbulent at the upper regions of the accelerated air stream. This turbulence in the upper regions of the accelerated air stream is an important factor to a process contributing to lift as will be explained.

Due to the attachment effect of the accelerated air stream through its boundary layer caused to flow over the upper surface la of the body 1, it is compelled to follow the curvature of the upper surface la ofthe body 1 such that when it reaches the lower rim lb of the upper surface it is already deflected in a downward or substantially downward direction and thus contributes to the lift imparted to the body 1 due to the upwardly directed reaction as it detaches from the upper surface la at the body's lower rim lb. An additional component of lift results by a process of air induction. As the accelerated air stream compelled to flow over and attached to the upper surface 1 a of the body 1 by the action of the disk fan air accelerating means 2, a degree of turbulence occurs in the upper region of the accelerated air stream as already stated. The consequence of this is that ambient air above the upper surface 1 a of the body 1 but which does not pass through the disk fan air accelerating means 2 is induced to enter the accelerated air stream and flow over the upper surface la as if it were so to do if it had passed through the disk fan air accelerating means 2.

The consequence of this is that a greater air mass is caused to flow over the upper surface 1 a of the body 1 in a downward direction than is drawn into the disk fan air accelerating means 2 thus adding to the air mass leaving the lower rim lb of the body 1 resulting in an additional component of lift being imparted to the aerial device.

The ambient air thus drawn into the accelerated air stream caused to flow over the upper surface la of the body 1 by the disk fan air accelerating means 2 results in a reduction in ambient air pressure above the body 1 and to some degree this reduction in ambient air pressure emends an area heater rl^lal the plan area of the body 1 and. esuAts in an additional component of lift acting over at least the total plan area of the aerial device.

Referring to figure 7, the overall result is that when a sufficient mass of air is drawn into the top of the disl: fan air accelerating means 2, the reaction force of the accelerated air stream flowing over the upper surface 1 a of the body 1 and leaving the upper surface 1 a at its lower rim lb assisted by the resulting air pressure reduction effect above the upper surface 1 a of the body 1 caused by turbulence in the upper regions of the accelerated air stream flowing over the upper surface la of the body 1 and inducing ambient air into the air steam, combined with the reaction to the suction force resulting when ambient air is drawn into the top of the disk fan air accelerating means 2 is greater than the total weight of the aerial device then the aerial device will ascend vertically due to these forces and this ascent will be sustained while these forces prevail.

Referring to figures 11, 12, 13 and 15, the present invention comprises improvements to aerial devices of circular, oval or polygonal plan form with a special convex curve to their upper surface that are able to ascend in a controlled manner by means of the surrounding air at the top being drawn into and accelerated over the curved upper surface and which attaches to the downwardly curved upper surface by aerodynamic effects and provides an upwardly directed reaction as it leaves the lower rim of the aerial device, as so far described, by the addition of a motor 5, a motor torque cancellation and steering device 8, and localised air stream detachment aerofoil means 6 and detachment aerofoil control actuators 7 mounted to the body 1 of the aerial device.

The motor 5 drives a radial air accelerating means which in this embodiment is a disk fan 2 such that air is drawn into the disk fan air accelerating means 2 coaxially and accelerated radially over the upper surface 1 a of the body 1 such that in so doing the accelerated air stream resows between one yaw adjusta'ole aerofoils Oa 1ol 1llirlg pal LS Or the motor torque cancellation and steering device 8 Referring to the partial view figure 13, the angle to which the yaw adjustable aerofoils 8a make to the accelerated air stream leaving the periphery of the disk fan air accelerating means 2 may be adjusted in either direction by rotating the yaw adjustable aerofoils control ring 8b about its vertical axis.

Referring to figures 13, 17 and 18, the action of the motor torque cancellation and steering device 8 is illustrated. As the yaw adjustable aerofoils control ring 8b is rotated about its vertical axis in either direction, as indicated by the curved arrows, then the yaw adjustable aerofoils 8a are caused to change their angle of yaw to the accelerated air stream leaving the disk fan air accelerating means 2, as indicated by radially pointed arrows over part of the upper surface la of the body 1. The consequence of this is that a rotation force is exerted on the body 1 such that it counters the torque caused by the motor and effects the steering of the aerial device.

Referring to figures 11, 12, 15, 20 and 21, the localised air stream detachment aerofoil means 6 and the detachment aerofoil control actuators 7 work together to effect control of lift and direction of horizontal travel. Figure 20 illustrates the action of the localised air stream detachment aerofoil means 6, uniformly lowered by the action of the detachment aerofoil control actuators 7. In this case, the accelerated air from the disk fan air accelerating means 2, as indicated by horizontally pointed arrows, is deflected over the localised air stream detachment aerofoil means 6 before the accelerated air stream is able

to attach to the upper surface la of the body 1. Consequently the lift force that would be exerted on the body 1 due to the combined actions of the air stream flowing over the upper surface la by the action ofthe disk fan air accelerating means 2, is negligible and hence the lilt illupal.ed to 'the ae.;a' device is minima! and the h^.zontal. force acting on the aerial device is equal and opposite in all horizontal directions and hence there is no tendency for the aerial device to ascend or to move horizontally.

Referring to figure 21, this illustrates the action of the localised air stream detachment aerofoil means 6, uniformly raised by the action of the detachment aerofoil control actuators 7. In this case, the accelerated a* from the disk fan air accelerating means 2, as indicated by the horizontally and downwardly pointed arrows is deflected under the localised air stream detachment aerofoil means 6 thus allowing the accelerated air stream to attach to the upper surface la of the body 1. Consequently the lift force exerted on the body l due to the combined actions of the air stream flowing over the upper surface 1 a is maximised and hence the lift imparted to the aerial device is a maximum, causing the aerial device to ascend, but the horizontal force acting on the aerial device is equal and opposite in all horizontal directions and hence there is no tendency for the aerial device to move horizontally.

The localised air stream detachment aerofoil means 6 may be positioned at any point between the extremes illustrated in figures 20 and 21 and consequently the lift imparted to the aerial device may be controlled by virtue of the uniform adjustment of the detachment aerofoil control actuators 7.

Referring to figure 19, which illustrates the action on the accelerated air stream leaving the disk fan air accelerating means 2 to effect horizontal motion of the invention by inclining to the horizontal, the localised air stream detachment aerofoil means 6 by the

independent action ofthe detachment aerofoil control actuators 7. On one side of the body 1 the accelerated air from the disk fan air accelerating means 2, as indicated by the horizontally pointed arrows, is deflected over the localised air stream detachment aerofoil means 6 before the accelerated air stream is aDie to aicacn to the uppei- s-urtace l a Or the body 1. Consequently, the lift force that would be exerted on this side of the body 1 due to the combined actions of the air stream flowing over this side of the body 1 upper surface 1 a is negligible and hence the lift imparted to the body 1 is minimal on this side of the aerial device. Whereas, on the other side of the body 1 the accelerated air from the disk fan air accelerating means 2, as indicated by the horizontally and downwardly pointed arrows is deflected under the localised air stream detachment aerofoil means 6 thus allowing the accelerated air stream to attach to the upper surface la ofthe body 1.

Consequently, the lift force exerted on this side of the body 1 due to the combined actions ofthe air stream flowing over the upper surface la is maximised and hence the lift imparted to the body 1 is a maximised on this side of the aerial device. In this way, the horizontal forces exerted on the body 1 due to the action of the accelerated air stream are no longer equal and opposite in all horizontal directions and consequently the aerial device is accelerated in the direction of the net force acting horizontally on the body 1.

The localised air stream detachment aerofoil means 6 may be positioned at any inclination between the extremes illustrated in figure 19 and in any direction and consequently the lift imparted to any side the aerial device may be controlled by virtue of the independent adjustment of the detachment aerofoil control actuators 7 and similarly the net horizontal force acting on the body 1 may be controlled to effect acceleration in any horizontal direction without the need point the aerial device in the preferred direction of travel.

Claims

1. Improvements to aerial devices of circular, oval or polygonal plan form with a special convex curve to their upper surface that are able to ascend in a controlled manner by means of the surr^'lnAdin.g air at the top being draws into and accelerated over the curved upper surface, by suitable means, and which then attaches to the downwardly curved upper surface by aerodynamic effects and provides an upwardly directed reaction as it leaves the lower rim of the aerial device by the addition of a motor to power the means of drawing in air and accelerate it over the curved upper surface, a motor torque cancellation and steering device and a localised air stream detachment aerofoil means, to effect localised detachment of the boundary layer air caused to flow over the upper surface of the aerial device by the air accelerating means and which controls the lift imparted to the aerial device as well as to effect steering of the aerial device.

2. Improvement to aerial devices as in claim 1 wherein the motor torque cancellation as well as steering of the aerial device is effected by an arrangement of yaw adjustable aerofoils in a vertically configuration around the air accelerating means such that a rotational force is exerted on the arrangement by the action of the accelerated air passing between the aerofoils and the magnitude and direction of the rotational force can be controlled by uniformly adjusting the yaw angle of the aerofoils with respect to the direction of the accelerated air stream.

3. Improvement to aerial devices as in all previous claims wherein the motor torque cancellation as well as steering of the aerial device is effected without the need for slipping clutches or friction plates or other means designed to facilitated the coupling of rapidly moving parts to control mean that are not in rapid motion.

4. Improvement to aerial devices as in all previous claims wherein the lift imparted to the aerial device is controlled by an arrangement of aerofoils in a horizontal configuration around the air accelerating means and which may be adjusted in height above the body of the aerial device by means of controlled actuators or by other means such that the accelerated air stream may be deflected away from the upper surface of the body of the aerial device by uniformly raising the aerofoil arrangement, and hence prevent the attachment of the accelerated air stream to the body of the aerial device, or adjusted in height above the body ofthe aerial device by uniformly lowering the aerofoil arrangement by the same means such that the accelerated air stream is allowed to attach to the body of the aerial device and thereby control the ascent or descent of the aerial device.

5. Improvement to aerial devices as in all previous claims wherein the ascent and descent of the aerial device is controlled without the need for slipping clutches or friction plates or other means designed to facilitated the coupling of rapidly moving parts to control mean that are not in rapid motion.

6. Improvement to aerial devices as in all previous claims wherein the horizontal propulsion imparted to the aerial device is controlled by an arrangement of aerofoils in a horizontal configuration around the air accelerating means and which may be adjusted in pitch in any direction by means of independently controlled actuators or by other means and with respect to the accelerated air stream caused to flow over the body of the aerial device by the action of the air accelerating means such that by so doing causes the horizontal forces acting on the aerial device to be imbalance and thereby propel the aerial device in the direction of the greatest horizontal force.

7. Improvement to aerial devices as in all previous claims wherein the horizontal propulsion of the aerial device is effected without the need for slipping clutches or friction plates or other means designed to facilitated the coupling of rapidly moving parts to coriLl-ol linear that are not in rapid 1lo'iOll.

8. Improvement to aerial devices as in all previous claims wherein the ascent and descent of the aerial device as well as the horizontal propulsion may be controlled by the same arrangement of aerofoils in a horizontal configuration around the air accelerating means.