GB2366274A

GB2366274A - A compact, economic and manoeuverable aircraft

Info

Publication number: GB2366274A
Application number: GB0021236A
Authority: GB
Inventors: Edmund Peter Gortowski
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-08-31
Filing date: 2000-08-31
Publication date: 2002-03-06
Also published as: GB0021236D0

Abstract

A manoeuvrable and relatively compact manned aircraft, which is intended for economic operation by means of providing a large component of the lift forces required by means of a buoyancy bag (or envelope) 1 containing a lighter than air gas, with the then relatively low residual lift and directional thrust required provided from a power driven source 7. There is a buoyancy bag with a people and machinery enclosure 2 underslung to provide stable operations. Lift and control thrust airflow created by fan 6 and controllable duct 8 pass through the body of the machine.

Description

<Desc/Clms Page number 1> A COMPACT, ECONOMIC AND MANOUEVRABLE AIRCRAFT This invention relates to a manoeuvrable and relatively compact manned aircraft, which is intended for economic operation by means of providing a large component of the lift force by being semi-buoyant in air.

There are many types of aircraft currently in operation, and they all have particular features. Most of these craft are entirely reliant upon the engine power to achieve dynamic (or aerodynamic) lift, such as propeller or turbine aeroplanes, and helicopters. To achieve the ability for low speed manoeuvrability and hovering generally requires a helicopter, which is both expensive to operate, and also requires high levels of maintenance. There are also buoyant (in air) craft, such as airships, but these are generally large.

An object of this invention is to provide a relatively small size of craft, which is both highly manoeuvrable, and is economic to produce and operate.

Accordingly, this invention utilises a buoyancy bag with a people and machinery enclosure underslung, and an engine driven ducted fan lift and control system, with the airflow through the craft.

Preferably, the machine will be constructed principally from modern lightweight materials, and the range of such suitable materials is quite wide.

A preferred embodiment of the invention will now be described with reference to the accompanying drawing in which: FIGURE 1 shows a cross-sectional side view illustrating the principle features.

As shown in Figure 1, the buoyancy bag 1 is attached to the underslung enclosure 2 which houses the pilot / driver 3 and passenger(s) 4, along with the driving machinery 7 enclosed within its safety protective housing to separate and segregate it from the people.

The buoyancy bag 1 provides lift to the aircraft by being filled (or partially filled) with a lighter than air gas (such as Hydrogen or Helium). This lift is intended to be less than or equal to the weight of the machine, so that the machine (when loaded ) then has an effectively low weight requiring to be lifted to become airborne. As the size of the bag would depend upon many features, this drawing is not to an exact scale.

To provide the required lift for the aircraft to become airborne, the engine and drive system 7, powers a fan 6 creating an airflow 5 through the machine, which exits via a controllable duct 8. When this duct outlet 8 faces downwards, and sufficient air flow and thrust are generated, the lift gained will raise the craft so that it becomes airborne.

To manoeuvre the aircraft, the controllable air duct (or nozzle) 8 can be swivelled in order to direct the thrust.

By these means the craft can be made to raise or lower, to fly backwards or forwards, to hover, or to travel either left or right. Or, a combination of these actions can be achieved. The pilot / driver controls a11 these functions from the control panel 9, at which place there are also the necessary controls and instruments to allow the aircraft to be driven / flown properly and safely. These would include such mechanical functions as engine and buoyancy monitoring, fuel levels, and navigation equipment such as height, bearing, rate of climb, and so forth. Under most conditions, it is expected that the aircraft would need radio communications equipment.

Also, as an aircraft, the machine would need to have certain mandatory features, such as navigation lamps, registration markings, and so forth.

Landing skids or wheels would be required, and arranged to suit the intended applications. Floats could be used in a "seaplane" application, for example.

For stability when "parked" upon the ground, the aircraft may carry an engine (or otherwise) driven high pressure pump, which could be used to deflate the buoyancy lift bag I and store the lighter than air gas in a high pressure cylinder. This cylinder could be permanently affixed to the enclosure. Re-inflation of the buoyancy bag I may then be achieved by a system of control valves connecting the high pressure cylinder to the buoyancy bag 1.

For safety, the aircraft could carry a parachute, which may then be deployed by the pilot in the event of an emergency, which would allow the machine to fall at a safer reduced speed (for example, when compared to a loss of buoyancy). A suitable place to locate this parachute would be on the upper side, such as in the ring around the air inlet 11, or another suitable place.

The buoyancy bag could be made in many shapes, and it is foreseen that a suitable layout would be an aerodynamic form, somewhat alike an "arrowhead" shape, as the machine would probably be used to fly forwards in most applications. However, where all round manoeuvrability is the goal (such as for survey or observation work, for example) then a more preferred shape may well be a flatten disc which moves equally well in all directions. The materials of construction should be chosen to provide an adequate margin of safety, and at the same time to be light. There is much engineering experience in these areas already, and it is expected that more will emerge as time passes.

The layout provides for intrinsic stability in the machine by locating the centre of gravity low within the overall form.

The enclosure 2 will obviously need to have door(s), windows, ventilation, and so forth to ensure that it is safe, functional and habitable. These highly obvious features will depend upon the exact layout for their detail embodiment, and are not shown upon the illustration to improve clarity.

The aircraft may have, in addition to the features noted above, external devices to aid navigation and control, and as these would depend upon the exact application, they are not shown.

Claims

CLAIMS l . A manoeuvrable and relatively compact manned aircraft, in which a large component of the lift forces required are produced by means of lighter than air gases within an envelope or bag providing buoyancy in air, with the remainder of the lift, and the directional drive, being provided by an engine or motor.
2. A relatively compact manned aircraft as claimed in Claim 1 which can be constructed in a variety of physical shapes and sizes, from a variety of materials, using the principles herein described y
3. A relatively compact manned aircraft as claimed in Claim 1 wherein there is an enclosure underslung below the buoyant canopy or bag to house people and machine:; a stable manner with respect to the centre of gravity.
4. A rclativelv compact manned aircraft as claimed in Claim 1 whcrcin +l-ere is a no;-#e:# ducted tin. drive through the. aircraft.
5. A relativel v compact manned aircraft as claimed in Claim I wherein there is an ability to add a driven gas pump which can transfer the lighter than air gases from the envelope to storeage, in order to reduce buoyancy when "parked" upon the ground - which process can of course be reversed for the addition of lift avaain when flight is required.
6. A relatively compact manned aircraft as described herein with references to Figure 1 of the accomnanvina drawing.