Aircraft with this VTOL technology can achieve VTOL even its thrust-to-weight ratio is smaller than 1

Abstract

An aircraft with this VTOL technology (the Invention) (6,7,8,9,10,18,19,20) can achieve VTOL even its thrust-to-weight ratio is smaller than 1. It is impossible for an aircraft with a thrust-to-weight ratio smaller than 1 to take off and land vertically with traditional technologies. The present invention, however, can achieve VTOL on these aircraft (6,7,8,9,10,18,19,20) by generating another lift force for VTOL by horizontally setting a Thin Wing (2) at the middle of the perpendicular line of the horizontal section inside the Air Intake Duct (5,6) in addition to the lift force obtained by traditional ways. This invention can be used to retrofit an existing aircraft to achieve VTOL or manufacture a VTOL aircraft with a thrust-to-weight ratio smaller than 1.

Description

This invention is to achieve VTOL (vertical take-off and landing) on aircraft whose thrust-to-weight ratio is smaller than 1.

Currently, VTOL is only possible for aircraft with a thrust-to-weight ratio equal to or greater than 1 because of the limitation of traditional VTOL technologies which, without exception, get the lift force in vertical direction for VTOL from a downward-directed propelling nozzle of a jet engine solely, or its combination with a lift fan.

The present invention, however, can achieve VTOL on aircraft whose thrust-to-weight ratio is smaller than 1. According to its first characteristic, this invention can obtain or generate another lift force for VTOL, in addition to the lift force obtained by traditional ways, by horizontally setting a Thin Wing at the middle of the perpendicular line of the horizontal section inside the Air Intake Duct.

According to the characteristics of the present invention, the following are true:

The Thin Wing is a part of the Air Intake Duct and is attached to the inner wall of the latter in a fixed or flexible way. The Thin Wing will produce a lift force when air flows over it and the produced lift force will be then transmitted to the inner wall of the Air Intake Duct to lift the aircraft off the ground.

The Thin Wing is designed such that its area and shape take into full consideration the air inflow of the jet engine and can ensure the produced lift force will be greater than the difference between the maximum take-off weight and the vertical thrust of an aircraft.

The entire or part of the Air Intake Duct with a Thin Wing can be fixed or formed through the transformation of components of an aircraft.

The entire or part of the Air Intake Duct with a Thin Wing can be fitted to the fuselage or wings of an aircraft.

The leading end of the Air Intake Duct with a Thin Wing in horizontal direction can be opened or closed.

The leading end of the Air Intake Duct with a Thin Wing in vertical direction can be opened or closed.

The attached figures are an illustration of this invention as follows:

FIG. 1 is a side view of an aircraft with this invention on ground (without landing gear) and during horizontal flight.

FIG. 2 is a front view of the transformable wings of an aircraft with this invention on ground and during horizontal flight.

FIG. 3 is a top view of the transformable wings of an aircraft with this invention on ground and during horizontal flight.

FIG. 4 is A-A Section for FIG. 3.

FIG. 5 is B-B Section for FIG. 3

FIG. 6 is a side view of an aircraft with this invention during vertical taking off and landing.

FIG. 7 is a front view of the transformable wings of an aircraft with this invention during vertical taking off and landing.

FIG. 8 is a top view of the transformable wings of an aircraft with this invention during vertical taking off and landing.

FIG. 9 is M-M Section for FIG. 8

FIG. 10 is N-N Section for FIG. 8

As illustrated in FIGS. 1, 2, 6 and 7, an aircraft with this invention is mainly made up of a fuselage (18), transformable wings (19), an extended section (6) of the air intake duct for the wing, an openable/closable leading end (8) of the air intake duct in horizontal direction and that (20) in vertical direction, a jet engine (7) with a propelling nozzle (10) that can be directed downward, and an APU (9) with a propelling nozzle (10) that can be directed downward. The air intake duct (5) formed by the transformable wing (19), together with the extended section (6) of the air intake duct for the wing, jointly forms an intake duct (5,6) with a thin wing (2) to produce an additional lift force besides the one produced by traditional technologies.

As illustrated in FIGS. 3, 4, 5, 8, 9 and 10, the transformable wing (19) is made up of a fixed wing (3), a hydraulic sleeve (1), a thin wing (2), a sliding wing (4), a leading edge flap (11,14) and a trailing edge flap (12,15), aileron (17) and hinge (13).

When taking off from the ground, the Fixed Wing (3) of the Transformable Wing (19) is fixed to the Fuselage (18), and the Sliding Wing (4) and Thin Wing (2), under the action of the Hydraulic Sleeve (1), will go down to a position where the Leading End (20) of the Air Intake Duct in vertical direction will open and the Jet Engine (7), with the Leading (8) End of the Air Intake Duct in horizontal direction closed, can freely take air in from the Air Intake Duct (5) of the Transformable Wing (19) at a flow rate enough for the Thin Wing (2) to produce a lift force for VTOL. At the same time, the upper (14) and lower part (11) of the Leading Edge Flap and the upper (15) and lower part (12) of the Trailing Edge Flap as well as the Aileron (17) begin to rotate around the Hinge (13) to increase the lift for the transition between vertical taking off/landing and horizontal flight. The Leading End (8) of the Air Intake to the Jet Engine (7) is closed to prevent the aircraft from horizontal movement and to increase the Air Flow (16) through the Air Intake Duct (5,6) with a Thin Wing (2). Also, the horizontal thrust generated by the Jet Engine (7) will be directed downward by the Propelling Nozzle (10). Then, the Jet Engine (7) starts to increase the thrust gradually. Now, the Air (16) flows through the Air Intake Duct (4) which is formed as the Sliding Wing and Thin Wing are going down. Because the velocity of the Air flowing over the upper surface of the Thin Wing (2) within the Air Intake Duct (5) of the Transformable Wing (19) is higher than that over the lower surface of the Thin Wing (2), and according to Bernoulli's Principle stating an increase in the speed occurs simultaneously with a decrease in pressure, we know that there will be a lift force produced on the wing due to the lower pressure on the upper surface of the Thin Wing (2) than that on the lower surface of the Thin Wing (2). And this Lift Force is then transmitted to the fuselage through the Hydraulic Sleeve (1) and Fixed Wing (3). Again, this force is never seen before and is an essential feature distinguishing the present invention from any other VTOL technology. The Thin Wing (2) is designed such that its area and shape take into full consideration the air inflow of the Jet Engine (7) and can ensure the produced lift force will be greater than the difference between the maximum take-off weight and the vertical thrust of an aircraft. The Air Intake Duct (5) of the Transformable Wing (19) is extended to the Jet Engine (7) through an extended section (6) (a suspended arm in this case). The air flows through the Air Intake Duct (5) of the Transformable Wing (19) and the Extended Section (6) (a suspended arm in this case) of the Air Intake Duct of the Wing and enters into the Jet Engine (7) where the air is burned and blown out of the Propelling Nozzles (10) which is now directed downward to generate lift force to lift the aircraft off the ground. There are now two lift forces to achieve VTOL, i.e. one generated by the Air (16) flowing through the Air Intake Duct (5,6) with a Thin Wing (2) and the other one generated by the high-temp burned air thrown out of the downward-directed Propelling Nozzles (10) of the Jet Engine (7) and APU (9). The Hydraulic Sleeve (1) now can drive the left and right Sliding Wing (4) to move up and down to balance the aircraft horizontally during vertical taking off and landing, correspondingly, the vertical balance can be controlled by adjusting the angle at which the Propelling Nozzles (10) of the Jet Engine (7) and APU (9) are directed downward.

A transition to horizontal flight from vertical taking off can be achieved by performing the above steps in reverse order. Similarly, a transition to vertical landing from horizontal flight can be achieved by repeating these steps.

All the formulas and calculations for this invention are listed in Annex 1.

All the formulas and calculations used to retrofit an Airbus A-380 based on this invention are listed in Annex 2.

This invention can be used to retrofit an existing aircraft to achieve VTOL or manufacture a VTOL aircraft with a thrust-to-weight ratio smaller than 1.

Claims

1. An aircraft, in which comprising innovative parts and an integral assembly as well as specific VTOL procedures and/or steps to achieve vertical taking-off and landing (VTOL) on aircraft of any type and having a thrust-to-weight ratio less than 1: Said aircraft comprising: the following innovative parts to generate lift for vertical taking-off and landing: transformable wings (19), which is made up of fixed wing (3), hydraulic sleeve (1), thin wing (2), sliding sing (4), leading edge flaps (11,14), trailing edge flaps (12,15), aileron (17), hinge (13), and which is capable of generating lift internally for vertical taking-off/landing by transforming during vertical taking-off/landing and of restoring its normal shape in order to reduce the drag during forward flight, a transformable fuselage (18), which is made up of a fixed fuselage, hydraulic sleeve (1), thin wing (2), a sliding fuselage, and which is capable of generating lift internally for vertical taking-off/landing by transforming during vertical taking-off/landing and of restoring its normal shape in order to reduce the drag during forward flight.And an integral assembly which is an integral part of the transformable wing (19) and transformable fuselage (18) and which is made up of the extended section of air Intake duct (6), the openable and closable leading ends of air intake duct in both horizontal and vertical directions (8 and 20), jet engine and auxiliary power unit (APU), both with downward deflectable propelling nozzles (10).And specific vertical take-off and land procedures and/or steps.

2. The aircraft according to above-mentioned claim, in which the opening and closing of the vertical leading end of the air intake duct on the fixed wing (3) is a direct result of the sliding of the sliding wing (4) over the fixed wing (3) under the action of the hydraulic sleeve (extending and retracting) to form and close the air Intake ducts (5).

3. The aircraft according to above-mentioned claims, in which the opening and closing of the vertical leading end of the air Intake duct on the fixed fuselage are a direct result of the sliding of the sliding fuselage over the fixed fuselage under the action of the hydraulic sleeve (extending and retracting) to form and close the air intake duct (5).

4. The aircraft according to above-mentioned claims, in which the thin wing within the transformable wings (19), during vertical taking-off or landing and under the extending of the hydraulic sleeve (1), is positioned in which the flat of the strings in the thin wing is equidistant with the parallel upper and lower wall within the air intake duct (5) that are formed by the fixed wing (3) and sliding wing (4). When the air flows through, according to the wall effect, the thin wing will, given a same velocity, have a greater lift than in the open air. During forward flight, the retracting of the hydraulic sleeve (1) will force the thin wing and sliding wing (4) within the transformable wing (19) to approach the fixed wing (3) until the upper surface of the thin wing clings to the lower wall inside the fixed wing (3) order to reduce the drag.

5. The aircraft according to above-mentioned claims, in which the thin wing within the transformable fuselage (18), during vertical taking-off or landing and under the extending of the hydraulic sleeve (1), is positioned in which the flat of the strings in the thin wing is equidistant with the parallel upper and lower wall within the air intake duct (5) that are formed by the fixed fuselage and sliding fuselage. When the air flows through, according to the wall effect, the thin wing will, given a same velocity, have a greater lift than in the open air. During forward flight, the retracting of the hydraulic sleeve (1) will force the thin wing and sliding fuselage within the transformable fuselage (18) to approach the fixed body until the lower surface of the thin wing clings to the upper wall inside the fixed fuselage in order to reduce the drag.

6. The aircraft according to above-mentioned claims, in which the vertical taking-off and landing procedure comprises the following steps: Taking off from rest on ground: