GB2390884A

GB2390884A - A VSTL aircraft

Info

Publication number: GB2390884A
Application number: GB0216471A
Authority: GB
Inventors: John William Rees
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-07-16
Filing date: 2002-07-16
Publication date: 2004-01-21
Also published as: GB0216471D0

Abstract

A very short take-off and landing aircraft comprises an airframe including a fuselage, fixed wings having leading edge slots (S), horizontal and vertical flying control surfaces and at least one fan (X) wherein the mass flow of air from the or each fan (X) is ducted to exit from the leading edge slots (S). Air may also be ducted to slots or gaps (G) in the elevator or rudder or to jets (R, Y, P) for attitude control.

Description

'it' -

A VERY SHORT TAKE-OFF AND LANDING AIRCRAFT

This invention relates to a very short take-off and landing aircraft.

There are many type-e of aircraft in general use. The tenn aircraft encompasses acroplanes of all descriptions, including helicopters, seaplanes, amphibious

vehicles, micro-lits, flying platforms and other vehicles that move from point to point, above the ground, supported by aerrodyramic principles.

A Sue helicopter generates aerodynamic lift by physical rotation of flying sf.aes supporting the aircraft. This principle allows vertical flight and is outside the realms of this invention.

There are, however, combination helicopters, which utilise rotary and fixed wags, these combination types come within the realms of this invention.

Aircraft whose engines develop thrust greater than the weight of the aircraft can also generate vertical piglet; these aircrafts are also outside the scope of this invention. All aircraft that would normally require a take-off run prior to becoming airborne, whether it be on land or sea, come within the scope of this invention.

Aircrafts that come within the scope of this invention, normally operate from prescribed airports, airfields, lakes or other places capable of providing the

necessary distance required for the take-off non. The length of the required take-on limits particular aircrafts to specific locations.

The shorter the required rake-off run; the greater is the number of locations available for the aircraft to operate from.

Aircraft that require long take-off run s are therefore handicapped to only operate from these larger areas prescribed locations.

Aircraft having the shortest take-off run requirements, have the greatest freedom in choice of where they may take-off and land. This is an advantage that can increase the utilisation and value of aircraft operations.

This invention allows aircrafts of various foe=, to be designed and constructed in such a mariner as to provide for extremely short take-off and landing runs, bestowing the aircraft with the advantage of being able to operate from the Sum number of sites.

This advantage allows fixed wing aircraft to compete with rotary wing aircraft in their utility role.

This advantage allows for point-to-point operation, eliminating the need for ground transportation at either end of the journey.

The present invention seeks to provide an aircraft with fixed wings and movable flying control surfaces to be capable of mininlising the take-off and landing distances required.

According to the invention, there is provided a very short take-off and landing aircraft comprising an airframe including a fuselage, fixed wings having wing leading edge slots, horizontal and vertical flying control surfaces and at least

f one fan, wherein the mass flow of air from the or each fan is ducted to exit from the wing leading edge slots. This blows air over the upper surface of the wings.

Preferably, the aircraft includes slots to which a proportion of the mass flow of ad from the or each fan is ducted to exit so as to blow over the horizontal and/or vertical flying control surfaces.

Advantageously, the or each fan is driven by one or more engines conveniently driven by the aircraft's engines or by one or more alternative power supplies.

The ducted fans may be the fans of high by-pass ratio jet engines, or any other fan capable of producing Me necessary air supply.

The or each fan is preferably provided with variable pitch control.

The or each fan is preferably prodded with variable helix control.

In one embodiment, means is provided for redirecting sir through alternative outlets to provide thrust for cruise conditions.

Air jet outlets are, preferably, located at various positions on the airfiame to facilitate attitude and orientation control by directing air through said jets.

In one preferred embodiment, means are provided for blouring air Mom the flap knees. Blowing of air over the wings and/or control surfaces is required for the short take-off Ed landing flight regimes and not necessarily for cruise flight regimes.

f For cruise conditions, blowing may cease with the air being redirected to provide direct thrust for forward flight.

An embodiment of the invention will now be described, by way of example only, with reference to He accompanying drawing which shows a perspective view of a short take off and landing aircraft according to Be present invention Referring to the drag, there is shown a very short take-off and landing aircraft The aircraft has a fuselage, fixed wings, elevators and rudder.

Within the fuselage there is an engine, E to drive the fan, X. The air from the Fin is dueled within the fuselage to the wing leading edge slots, the flying control surfaces; mewing the elevators and rudder, and the attitude control jets, R=Y and P. The slots, S are hill span width, sized to provide the optimum mass flow at optimism air-speed and pressure necessary to create the maximum lift, by virtue of minimum pressure above the wing. The jets, R provide enhanced roll control and assist aileron control.

The elevator and rudder slots, G are closed in the neutral position and open automatically, either side of the control surface according to the flight controls position. In the elevator up position, the slots will allow air to exit below the elevator, creating a downward force on the tail. The jets, P assists the pitch control provided by the elevators. The jets, Y assists me yaw control provided by the rudder.

THE ADVANTAGES of blowing air over an aerofoil is firstly to maintain the adhesion of the flow over the surface, secondly to create a low pressure in this region and thirdly to entrain the surrounding air to more rapidly extend this low-pressure area

Claims

r CLAIMS

1. A very short take-off and landing aircraft comprising an airframe including a fuselage, fixed wings having wing leading edge slots, horizontal and vertical flying control surfaces and at least one fan, wherein the mass flow of air from the or each fan is ducted to exit from He wing leading edge slots.

2. A very short take off end landing aircraft as claimed in claim 1, including slots to which a proportion of the mass flow of air from the or each fan is ducted to exit so as to blow over the horizontal and/or vertical flying control surfaces.

3. A very short take-off and landing aircraft as claimed in claim 1 or claim 2, wherein the or each fan is Given one or more engines.

4. A very short talcemff and landing aircraft as claimed in any preceding claim, wherein We or each fan has variable pitch control.

A very short take-off and landing aircraft as cloned in any preceding claim wherein the or each [an has variable helix control.

6. A very short take-off and landing aircraft as claimed in any preceding claim, wherein means is provided for redirecting air through alternative outlets to provide thrust for cruise conditions.

7. A very short take-off and landing aircraft as claimed in any preceding claim including air jet outlets located at various positions on the airframe to facilitate attitude and orientation control by directing air Trough said jets.

8. A very short take-off;md landing as claimed in any preceding claim, including means for blowmg air Tom the flap knees.

9. A very short take-off end landing aircraft substantially as described herein with reference to Me accompanying drawing.